20060512000282006051200028CE  2006       5          12         000              120060331G321351410051        BOLT            CESSNA                  CESSNA421   421A        2076012CE  CONT  O520  GTSIO520*   17032SO                              RT MLG          DEPARTED        P      K   NONE                                                                                            O  OTHER                                                                         TXTAXI/GRND HDL  1                      SO19849JB2000 2000  NA          421A0075                                WHILE TAXING TO PARK THE RT MLG LINK ASSEMBLY BOLT CAME OUT CAUSING THE UPPER AND LOWER LINKS TO SEPERATE. THE RT LANDING GEAR TURNED 90 DEGREES BENDING THE GEAR DOOR COVER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1L72 3O3  O  A7CE    E7CE                 
20060608004422006060800442GL  2006       6          8          000000002        120060530G32222032200800      FORK            DIAMON                  DIAMONDA20  DA20C1      2990001GL                                                               NOSE WHEEL      CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL09857PA1544                   C0218                                   DISCOVERED 8 CRACKS, 4 PER SIDE APPROXIMATELY 1 INCH FORWARD OF NOSE GEAR AXLE ADJACENT TO FAIRING ATTACH POINT HOLES.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L71 3O    NTTA4CH                        
20060613001962006061300196GL  2006       6          13         0079965A         320060404G6114E71693          HUB                                     BEECH 58    58P         1152744CE                                   HARTZLHCJ3Y PHCJ3YF2    GL  PROPELLER       CORRODED        B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW99                                                                    PROPELLER HUB HAS INTERNAL AND EXTERNAL CORROSION                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L72 3O      A23CE           5  CP36EA    
20070613001612007061300161NE  2007       6          13         0089756          320060203G611194LMA4          BLADE                                   CESSNA425   425         2076018CE                                   MCAULY4HFR344HFR34C762  NE  PROPELLER       CORRODED        B  EY2RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03                                                    951649          CORROSION IN BLADE SHANK, NOT REPAIRABLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 3T    RTA7CE            6  C3PNE     
20070613001602007061300160GL  2007       6          13         0093855          320061103G6114D2011           HUB             HARTZL                  BEECH 58    58          1152740CE                                   HARTZLHCC2Y BHCC2YF2    GL  PROPELLER       CORRODED        B  EY2RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03                                                    AN737           HUB CORRODED BEYOND SPEC.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 3O      3A16            5  CP920     
20060627003322006062700332CE  2006       6          27         01676201         120060621G3213NAS464414       BOLT            CESSNA                  CESSNA421   421A        2076012CE                                                               ZONE 700        FAILED          B  DYCRE   ENGINE SHUTDOWN                                                                                 G  MULTIPLE FAILURE                                                              TXTAXI/GRND HDL  1                      GL07216WA3463                   421A0032                                LANDING GEAR COLLAPSED DURING ROLLOUT AFTER LANDING. UPON INSPECTION IT WAS NOTED THAT A BOLT CONNECTING THE DOWNLOCK BELLCRANK TO THE UPPER STRUT ASSEMBLY HAD FAILED. THE BOLT HEAD WAS MISSING ALLOWING ALL OF THE FORCE FROM THE BELLCRANK TO BE APPLIED DIRECTLY AND ENTIRELY TO THE FORWARD ATTACH LUG ON THE UPPER STRUT CAUSING THE LUG TO BREAK AND THE GEAR TO COLLAPSE. MAINTENANCE RECOMMENDS TIME CHANGE ON BOLT AND AN NDT INSPECTION OF LUGS AND SURROUNDING AREA AT THE SAME TIME.                                                                                                                                                                                                                                              1L72 3O      A7CE                         
20060512000382006051200038SO  2006       5          12         0600710          120060331G781089366003        EXHAUST RISER                           PIPER PA44  PA44180     7104402SO  LYC   O360  LO360E1A6   41514EA  HARTZLHCC3Y HCC3Y*      GL  RT ENGINE       BROKEN          B  BF8XA   UNSCHED LANDING                                                                                 ER VIBRATION/BUFFET          PARTIAL RPM/PWR LOSS                                CRCRUISE         1                      WP07572ER2449                   4496148     L74571A     AU10894B        PILOT'S REPORTED VIBRATION IN RT ENGINE, ALSO STATED SOMETHING SEEMED LOOSE AND RATTLING. LEANED AT DIFFERENT POWER SETTINGS WHILE IN FLIGHT WITH NO CHANGES. RETURNED TO AIRPORT WITHOUT INCIDENT. UNCOWLED RT ENGINE AND FOUND NR 2 CYLINDER EXHAUST RISER BROKEN OFF AT MOUNT FLANGE. REPLACED WITH NEW RISER AND GASKET, OPERATIONAL CHECK GOOD.                                                                                                                                                                                                                                                                                                                                                                                            1L72 3O3  O  A19S0   E286    5  CP25EA    
20060913002352006091300235NM  2006       9          13         060602           120060909G531013017R          RIB                                     UNIVAR415   415C        0420302NM                                                               CENTER SECTION  CORRODED        D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW1599325                       1948                                    THE DEFECT WAS DISCOVERED DURING THE INITIAL COMPLIANCE WITH AD 2002-26-02 ON AN AIRCRAFT THAT HAD BEEN IN STORAGE FOR A NUMBER OF YEARS. AN APPROXIMATE 0.5 INCH BY 0.25 INCH AREA AT THE BOTTOM EDGE OF A LIGHTENING HOLE WAS CORRODED AND FLAKING. A COLLECTION OF NUT SHELLS AND DEBRIS WERE FOUND NEARBY, INDICATING THAT THE CORROSION WAS PROBABLY STARTED DUE TO THE PRESENCE OF ANIMAL WASTE PRODUCTS AND THE BLOCKAGE OF DRAINAGE PATHS. STORAGE IN A RODENT-CONTROLLED AREA, COMBINED WITH PERIODIC USE OF INSPECTION HOLES (WHICH WERE INSTALLED TO COMPLY WITH THE AFOREMENTIONED AD) TO APPLY CLEANING FLUIDS AND CORROSION PREVENTIVE COMPOUND SHOULD HELP PREVENT FUTURE RECURRENCE.                                            1L71 3O      A718                         
20060718001632006071800163CE  2006       7          18         071106KTR        120060410G3210AN501A105       SCREW                                   BEECH MU300 400A        1155402CE                                                               LANDING GEAR    SHEARED         B  NV2RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE07                                                                    UPON REMOVAL OF THE PLUNGER TUBE ASSEMBLY FROM THE LANDING GEAR CYLINDER, FOUND THE2 AN501A10-5 SCREWS THAT SECURE THE PLUNGER TUBE HEAD TO THE PLUNGER TUBE HAD SHEARED. THE CONDITION RESULTED IN LOOSE PARTS, WHICH CAUSED ONLY MINIMAL INTERNAL STRUT DAMAGE, AND AFFECTED THE SHOCK CHARACTERISTICS OF THE AFFECTED LANDING GEAR STUT.                                                                                                                                                                                                                                                                                                                                                                                                     2H72 4F    RTA16SW                        
20060814001462006081400146CE  2006       8          14         080106           120060801G29101015802181      TUBE                                    BEECH 200   B200        1152922CE                                                               HYD SYSTEM      DAMAGED         B      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CE016300F538                    BB1865                                  DURING ROUTINE INSPECTION IT WAS DISCOVERED THAT THE PILOT SIDE RUDDER CABLE HAD BEEN RUBBING ON THE PILOTS SIDE RT BRAKE TUBE ASSY P/N 101-580218-1 NEAR THE FORWARD END OF THE TUBE ASSY CAUSING IT TO BECOME NOTCHED.  THE DAMAGE IS TO THE EXTENT THAT REPLACEMENT WAS REQUIRED. THIS DAMAGE WAS FOUND UNDER THE PILOTS SEAT FLOOR INSPECTION PANEL ADJACENT TO THE BUSS FEEDER DIODE ASSY.  THE CAUSE APPEARS TO BE IMPROPER TUBE ASSY ROUTING BY NOT ALLOWING FOR PROPER CONTROL CABLE CLEARANCE.  RECOMMEND INSPECTION OF THE AFFECTED AREA AND REROUTING AND OR REPLACEMENT OF BRAKE TUBE ASSY.                                                                                                                                         1L72 4T      A24CE                        
20060825000272006082500027GL  2006       8          25         0823061          320060823G6114D2A34C98NO      HUB             MCAULY      D2A34C98NO                                                                      MCAULY2A34C D2A34C98    GL  PROPELLER       CRACKED         B      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO17F-GAP           739321                              739321          CRACKED IN BLADE SOCKET.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     5  CP3EA     
20060614001882006061400188CE  2006       6          14         0MKR20064        120060525G551145A21104641     RIB             BEECH                   BEECH MU300 400A        1155402CE                                                               HORIZ STAB      CRACKED         B  OMKRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM03793TA           RK224       RK244                                   LT IB ROLLER SUPPORT RIB FOUND CRACKED.  P/N 45A21104-641 WAS REMOVED AND REPLACED WITH NEW.  DUE TO THE NUMBER OF THESE WE ARE SEEING, IT IS LIKELY THE ENTIRE 400A FLEET HAS A PROBLEM IN THIS AREA.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2H72 4F    RTA16SW                        
20060123002282006012300228CE  2006       1          23         1054822          120060110G5341                FRAME                                   LEAR  35    35LEAR      5170600CE  GARRTTTFE731TFE73122B   01518WP                              WING ROOT       CRACKED         B  WTXRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM074358N                       35065       74505                       FOUND CRACKS ON THE FUSELAGE SIDE OF FRAME 20 ON BOTH LT AND RT SIDE. FRAME 20 IS THE WING ATTACH POINT.  ON THE LT SIDE THE LENGTH OF THE CRACK WAS 1.25 INCH IN LENGTH AND ON THE RT SIDE, 1.50 INCH.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  F  A10CE   E6WE                 
20060123002292006012300229CE  2006       1          23         10548226         120060110G5341                FRAME                                   LEAR  35    35LEAR      5170600CE  GARRTTTFE731TFE73122B   01518WP                              WING ROOT       CRACKED         B  WTXRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM074358N                       35065       74505                       FOUND CRACKS ON THE FUSELAGE SIDE OF FRAME 20 ON BOTH LT AND RT SIDE.  FRAME 20 IS THE WING ATTACH POINT.  ON THE LT SIDE THE LENGTH OF THE CRACK WAS 1.25 INCH IN LENGTH AND ON THE RT SIDE, 1.5 INCH.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  F  A10CE   E6WE                 
20060214002142006021400214SO  2006       2          14         10943282         120060120G5310                FRAME                                   MAULE M5    M5210C      5460134SO  CONT  IO360 IO360*      17025CE                              FUSELAGE        CRACKED         B  WTXRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM03314X                        6134C                                   FOUND CRACK APPROXIMATELY .3750 INCH IN LENGTH ON RT FRAME 20 WING ATTACH POINT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1H71 3O3  O  3A23    E1CE                 
20060323000572006032300057CE  2006       3          23         11143            120060223G5341251120015       FITTING                                 LEAR  35    35A         5170602CE  GARRTTTFE731TFE73122B   01518WP                              FUSELAGE        CRACKED         C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM0781FR                        081                                     LT AND RT WING ATTACH POINT FITTING AT FRAME 20 IS CRACKED. LT IS CRACKED APPROX. 1.0 INCHES IN LENGTH.  RT IS CRACKED APPROX. 1.25 INCHES IN LENGTH.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F4  F  A10CE   E6WE                 
20060518002532006051800253CE  2006       5          18         11221            120060414G5311                FRAME                                   LEAR  35    35A         5170602CE                                                               FUSELAGE        CRACKED         E  WTXRK   NONE                                                                                            O  OTHER                                                                         UKUNKNOWN        1                      NM0798LC                        077                                     RH FUSELAGE FRAME 20 CRACKED APPROX. 11/8 IN LENGTH AT THE AFT WING ATTACH POINT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F      A10CE                        
20061018000602006101800060CE  2006       10         18         1538T092806      120060928G2120CM321110B335    DUCT                                    CESSNA421   421B        2076014CE                                                               RIGHT           BLOWN           D      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      GL111538T1764 176               421B0308                                CABIN BEGAN TO CLIMB AT 2000 FPM DURING CRUISE AT 12,500 FT.  DESCENT TO 10,500 FT.  CABIN WOULD ONLY MAINTAIN 2.5 PSID.  CHECKED OUTFLOW AND SAFETY VALVES, MOISTURE DRAINS, LANDING GEAR BOOTS, FAILEADS ALL FOUND OK.  PERFORM GROUND CHECK OF SYSTEM FOUND NO AUDIBLE LEAKS ELSEWHERE IN CABIN AND DIFFERENTIAL CHECKED OK. PERFORMED SECOND GROUND CHECK AND PULLED CABIN AIR VALVES ONE AT A TIME ISOLATED PROBLEM TO RIGHT SOURCE.  FOUND DUCT PARTIALLY BLOWN OFF OF SONIC VENTURI.  REMOVED DUCT AND FOUND .7500 INCH TEAR WHERE IT PASSES THROUGH WING RIB.  MFG NO LONGER STOCKS A 33.5 DUCT, ONLY 38 INCH. -38 CUT DOWN IN THE FIELD AND INSTALLED BOTH WINGS.  LT DUCTING REPLACED MARCH 2006.  RT DUCTING WAS FOUND AIRWORTHY AT T1L72 3O      A7CE                         
20060725001842006072500184CE  2006       7          25         15462006H1       120060710G80106041H190        RELAY                                   BEECH 200   A200        1152921CE                                                               NR 2 STARTER    BURNED          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW991546                        BC58                                    NR 2 START RELAY SHORTED TO GROUND DURING ENGINE START, APPARENTLY DUE TO WATER INCURSION OR CONTACT CORROSION. RELAY BURNED BUT START WAS SECURED BEFORE ADJACENT WIRE BUNDLE WAS DAMAGED. RELAY REPLACED. NEW RELAYS APPEAR TO HAVE ADDITIONAL SEALANT TO PREVENT THIS PROBLEM. MAY BE RELATED TO CORROSIVE ATMOSPHERE AS 2 OTHER IDENTICAL AIRCRAFT HAVE HAD SIMILAR FAILURES CAUSING MORE SEVERE DAMAGE AT THIS SITE.                                                                                                                                                                                                                                                                                                                       1L72 4T      A24CE                        
20060512001482006051200148EU  2006       5          12         1MAC06           120060410G2731T700A2740085002 CABLE                                   SOCATATBM   TBM700      8682000EU  PWA   PT6   PT6A64           EA  HARTZLHCE4N HCE4N3      NE  ELEV TRIM SYS   FRAYED          B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL11930MA201  100               340         PM0222      HH2276          FRAYED ELEVATOR TRIM CABLE FOUND DURING 100 HR INSPECTION IN AFT FUSELAGE ACCESS PANEL.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L71 3T4  TRTA60EU   E4EA    5  CP10NE    
20060518002452006051800245NM  2006       5          18         200600005        120060427G57309006031         PANEL                                   LKHEEDP3A   P3A         5260103NM                                                               LT WING         CRACKED         B  AUCRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP25925AU16997                  151361                                  NR 2 FUEL CELL LOWER WING SKIN, PLANK NR 2 CRACKED RISER. NO SRM STANDARD REPAIR FOR THIS DAMAGE. REPAIR WILL BE ACCOMPLISHED IAW  EO 462557001.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L74 4T    RTA32NM                        
20060921001242006092100124WP  2006       9          21         200600077        120060919G273078213008        HINGE                                   FRCHLDC82   C82ASTWDAVIS3372004WP  PWA   R2800 R2800*      52026NE                              ZONE 300        FRACTURED       B  KGBRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM049701F                       4557814                                 LT AND RT FURTHEST OB ELEVATOR HINGE BRACKET ON THE STABILIZER WERE BROKEN.  IT APPEARS TO BE FROM WIND GUSTS.  THE CENTER 3 HINGES WERE UNAFFECTED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2H73 4R4  RJ AR15    5E8                  
20060518002542006051800254EU  2006       5          18         20060502D        120060502G5313                LONGERON                                LET   L23   L23         1360308EU                                                               REAR COCKPIT    CRACKED         B  PF5RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM03420BA                       029007                                  FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LT RUDDER PEDAL, DURING A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF ALL MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT WHILE ACTUATING THE RUDDER PEDAL, CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCREWS.                                                                                                                                                                                                                                             1K00       RCG24EU                        
20060411000352006041100035SO  2006       4          11         2006ADP001       220060224G8530655470A3        CYLINDER                                CESSNA206   TU206G      2073357CE  CONT  O520  TSIO520M    17040SO                              ENGINE          CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP21     301                    U20606365   532260                      ALL SIX CYLINDERS HAVE CRACKS IN THE SAME AREA JUST ABOVE THE TOP SPARK PLUG HOLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O3  O  A4CE    E8CE                 
20060815000122006081500012    2006       8          15         2006ADP08001     420060804G2300                ELEC CONNECTOR                          DIAMONDA40  DA40        2990002GL                                                                               SHORTED         B      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      CE0538CF                        40567                                   ADJACENT MIC AND PHONE JACKS SHORTED TOGETHER CAUSING SQUEAL IN AUDIO SYSTEM.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1L71 3O    NTA47CE                        
20060926000312006092600031SO  2006       9          26         2006ADP09001     220060901G7497108326841       WIRE HARNESS                            CESSNA206   TU206G      2073357CE  CONT  O520  TSIO520M    17040SO                              IGNITION SYS    CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM08PKMAR94   94                U20606231   532296                      DURING INSPECTION ON A NEW, LOW TIME ENGINE, THE MT NOTICED A RATHER LARGE CRACK IN THE RT IGNITION HARNESS COVER, WHERE THE HARNESS ATTACHES TO THE MAGNETO.  AFTER LOOKING A LITTLE CLOSER, IT IS CLEAR THAT THE CRACK WAS THERE PRIOR TO OVERHAUL AND PAINTING.  THIS HARNESS WAS SUPPLIED WITH THE NEW ENGINE NOTED BELOW.                                                                                                                                                                                                                                                                                                                                                                                                                  1H71 3O3  O  A4CE    E8CE                 
20060411000392006041100039NE  2006       4          11         2006F00011       220060223G8530327628          CYLINDER                                DOUG  DC6   DC6B        3021712WP  PWA   R2800 CB3         52026NE                              NR 2 ENGINE     CRACKED         I      E   ENGINE SHUTDOWN                                                                                 R  PARTIAL RPM/PWR LOSS                                                          CRCRUISE         1                      AL05444CE     2269              45478       NK510061                    NR 2 ENGINE SHUT DOWN DUE ROUGH RUNNING                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L74 4R4  R  6A4     E264                 
20060804000112006080400011CE  2006       8          4          2006F00024       120060505G5100                CANISTER                                BEECH 300   300BEECH    1152930CE                                                               COWL            OPEN            E      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO0352LP                        FA8                                     SMOKING ON SHUT DOWN.  OPENED RIGHT SIDE COWLING AND FOUND THE END OF THE EPA CAN COMPLETELY OPEN.  END PLATE FOUND IN BOTTOM OF COWLING.  TT PRESUMED TO BE ORIGINAL.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4T      A24CE                        
20061012001192006101200119    2006       10         12         2006F00042       120060930G26122158            SMOKE DETECTOR                                                             PWA   PT6   PT6A42      52043NE                                              FALSE INDICATIOND      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            APAPPROACH       1                      GL07200E 6819                               PCE93694                    LT ENGINE FIRE INDICATION IN DECENT DURING APPROACH PHASE OF FLIGHT. SHUT ENGINE DOWN.INSPECTION OF THE FIRE DETECTION SYSTEM AND DETECTORS PROVED TO HAVE NO ISSUES, COULD NOT DUPLICATE ON GROUND RUN.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               4  T          E4EA                 
20061023000762006102300076EU  2006       10         23         2006F00048       120060925G28416653505509      PROBE                                   ISRAEL1124  1124A       4500103EU                                                               FUEL SYSTEM     MALFUNCTIONED   E      O   OTHER                                                                                           O  OTHER                                                                         LDLANDING        1                      SW09211ST8445                   303                                     PRIOR TO REFUELING AIRCRAFT, CREW NOTICED LEFT FUEL QUANTITY GAUGE WAS 1400 LBS HEAVIER THAN RIGHT.  SUBMITTED SPECIAL FLIGHT PERMIT AND RETURNED TO BASE.  FOUND LEFT MAIN FUEL PROBE BAD.  REMOVED AND REPLACED FUEL PROBE, CALIBRATED FUEL QUANTITY SYSTEM.  PERFORMED FUNCTIONAL CHECK FLIGHT, NO DEFECTS NOTED.                                                                                                                                                                                                                                                                                                                                                                                                                            2M72 4F      A2SW                         
20060105002112006010500211CE  2006       1          5          2006FA0000002    120060104G2497593240101       CIRCUIT BREAKER                         CESSNA421   421B        2076014CE  CONT  O520  GTSIO520C   17032SO                              MASTER          CORRODED        D      H   DEACTIVATE SYST/CIRCUITS                                                                        O  OTHER                                                                         NRNOT REPORTED   1                      EA01678DB4950                   421B0876                                AVIONICS MASTER CIRCUIT BREAKER SWITCH FOUND INTERMITTENT DURING COMPLIANCE WITH AD 2005-20-05, MEB05-1.  PN 593-240-101 NOT FOUND IN MFG PARTS MANUAL BUT THIS WAS CLEARLY THE ORIGINAL FACTORY INSTALLED CB.  PROBLEM NR1,  INTERNAL COMPONENTS OF CB HAD SEVERE CORROSION AND WAS CONTAMINATED WITH DUST, DIRT AND SMALL INSECTS.  AIRCRAFT HAS ALWAYS BEEN HANGARED EXCEPT ON TRIPS.  PROBLEM NR2  MEB 05-1 AND AD 2005-20-05 DO NOT INCLUDE THIS PART NUMBER.  THE AD AND MEB REFERENCE 539-250-101 (50 AMP BREAKER) NOT THE 40 AMP BREAKER FOUND ON ALL 421B AIRCRAFT (IAW THE MFG PARTS MANUAL).                                                                                                                                         1L72 3O3  O  A7CE    E7CE                 
20060106000112006010600011SO  2006       1          6          2006FA0000003    220060104G8550                DIPSTICK                                CIRRUSSR    SR22        2130001GL  CONT  O550  IO550*           SO                              OIL CAP         BROKEN          C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO115175L168                    1542                                    DURING PREFLIGHT WHILE CHECKING OIL LEVEL ON DIPSTICK, ENTIRE ROD PORTION OF DIPSTICK CAME APART IN MY HANDS UPON LIFTING IT OUT OF OIL FILLER TUBE.  BARELY CAUGHT IT WITH MY HAND BEFORE IT WOULD'VE FALLEN DOWN INSIDE THE ENGINE CRANKCASE WITH POTENTIALLY CATASTROPHIC RESULTS.  ROD IS SWAGED IN 2 PLACES ONTO A LOWER CALIBRATED AREA FOR DETERMINING OIL LEVEL AS WELL AS AT TOP WHERE IT AFFIXES TO DIPSTICK COVER.  IT HAS COME UNSWAGED IN BOTH UPPER AND LOWER PLACES.  IF THIS OCCURRED IN FLIGHT, IT APPEARS A CATASTROPHIC ENGINE FAILURE COULD OCCUR AS METAL ROD PARTS FELL DOWN INTO ENG CRANKCASE/SUMP REGION.  BELIEVE THIS DESERVES AN EMERGENCY AD.  THIS PLANE IS A 2005 - JUST A FEW MONTHS OLD!                       1L71 3O3  ONTA00009CHE3SO                 
20060110001412006011000141SO  2006       1          10         2006FA0000004    220060104G8550                DIPSTICK                                CIRRUSSR    SR22        2130001GL  CONT  O550  IO550*           SO                              ENGINE          BROKEN          C      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO115175L168                    1542                                    DURING PREFLIGHT WHILE CHECKING OIL LEVEL ON DIPSTICK, THE ENTIRE ROD PORTION OF THE DIPSTICK CAME APART IN MY HANDS UPON LIFTING IT OUT OF THE OIL FILLER TUBE. BARELY CAUGHT IT WITH MY HAND BEFORE IT WOULD'VE FALLEN DOWN INSIDE THE ENGINE CRANK CASE WITH POTENTIALLY CATASTROPHIC RESULTS.  ROD IS SWAGED IN 2 PLACES ONTO A LOWER CALIBRATED AREA FOR DETERMINING OIL LEVEL AS WELL AS AT THE TOP WHERE IT AFFIXES TO THE DIPSTICK COVER.  IT HAS COME UNSWAGED IN BOTH UPPER AND LOWER PLACES.  IF THIS OCCURRED IN FLIGHT, IT APPEARS A CATASTROPHIC ENGINE FAILURE COULD OCCUR AS THE METAL ROD PARTS FELL DOWN INTO THE ENGINE CRANK CASE / SUMP REGION.                                                                            1L71 3O3  ONTA00009CHE3SO                 
20060123002262006012300226CE  2006       1          23         2006FA0000015    120060104G5210                DOOR                                    AYRES S2    S2R         7630202CE  PWA   R1340 R1340*      52016NE  HAMSTD23D   23D40       NE  RT CABIN DOOR   BULGED          D      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      AGAGRICULTURE    1                      SW154914X                       2105R                                   CARBON MONOXIDE ENTRANCE INTO CABIN AREA.  INCREASED AIRSPEED RESULTING FROM THIS COMBINATION CAUSED THE RT CABIN DOOR TO BULGE SLIGHTLY.  PILOT CONCERNS ABOUT CARBON MONOXIDE ENTRANCE INTO THE CABIN WERE CONFIRMED WITH THE USE OF CO DETECTORS.  RT CABIN DOOR WAS REMOVED AND SENT TO SERVICE CENTER TO BE MODIFIED TO THE 2-LATCH CONFIGURATION FOUND ON TURBINE AIRCRAFT.  ADDITIONAL MONITORING FOR CARBON MONOXIDE SHOWED NO FURTHER PROBLEMS.                                                                                                                                                                                                                                                                                        1L71 3R3  RNCA4SW    5E2     6  CP719     
20060120001072006012000107CE  2006       1          20         2006FA0000018    120060111G282012161074        SEAL                                    CESSNA182   182M        2072728CE                                                               SELECTOR VALVE  DEFORMED        D      K   NONE                                                                                            WK INADEQUATE Q C            FLUID LOSS                                          ININSP/MAINT     1                      CE07                7069                                                RESEALED FUEL SELECTOR VALVE PN 0716613-1 AND DURING A LEAK TEST LEAKAGE WAS FOUND FROM ONE OF THE PN 1216107-4 SEALS. INVESTIGATION FOUND THAT THE SEAL FACE WAS DEFORMED AND THAT MOLD LINES FROM THE INJECTION MOLDING PROCESS CAUSED VOIDS IN THE SEALING SURFACE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3O    NT3A13                         
20060124001502006012400150GL  2006       1          24         2006FA0000019    120060109G3220                ROLL PIN                                DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240A           SO                              NLG STRUT       MISSING         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM03917AF                       C0172                                   ROLL PIN LOCKING THE NOSE STRUT ELASTOMERIC SPRING PLATE (PN 20-3220-05-02) TO THE SHOCK ABSORBER ROD (PN 20-3220-05-01) HAD WORKED OUT UNLOCKING THE ASSY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L71 3O3  ONTTA4CH   E7SO                 
20060124001982006012400198CE  2006       1          24         2006FA0000021    120060104G3242952891          BRAKE ASSY                              CESSNA195   195A        2073110CE  JACOBSR755  L4*         35003EA                              WHEEL           CORRODED        D      K   NONE                                                                                            O  OTHER                                                                         LDLANDING        1                      NM071528D3075                   7750                                    DISASSEMBLED BRAKE AND FOUND THAT THE BRAKE CYLINDER WAS CORRODED FROM WHERE THE O-RING MAKES A SEAL TO THE IB STOP. THE O-RING WAS HARD AND HAD TAKEN A SET.  MFG P/N 0341015.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1H71 3R3  R  A790    TC121                
20060124001182006012400118    2006       1          24         2006FA0000030    120060112G3242244688          KEYWAY          BFGOODRICH                                                                                                              STATOR/CARRIER  CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15                                                                    HAVE RECENTLY SEEN (4) BRAKE ASSY'S COME IN WITH THE CARRIER LINING/STATOR COMPLETELY BROKEN WITH MULTIPLE CRACKS AND DISCOLORED FROM WHAT APPEARS TO BE (OVERHEATED).  THESE PARTS ARE NOT LIFE LIMITED AND ARE ON CONDITION ONLY.  THEY ARE NDI AT THE TIME OF OVERHAUL BUT WITH THE AGING FACTOR AND OVERHEAT CONDITIONS, THESE PARTS WILL CONTINUE TO FAIL AND CRACK.  THE TABS ARE COMPLETELY SHEARING OFF AND COULD CAUSE SEVERE BRAKING FAILURE OF THE AIRCRAFT.  RE: W122086, W122087, W121926                                                                                                                                                                                                                                                                                    
20060124001202006012400120    2006       1          24         2006FA0000031    120060112G2120                SMOKE                                                                                                                                   COCKPIT         DETECTED        C      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      NRNOT REPORTED   1                      WP15                                                                    SMOKE IN COCKPIT FROM AUXILIARY GENERATOR OIL SPILL.  2ND TIME FOR AA MD80 IN LAST 30 DAYS.  FLIGHTS:  AA1160 12/14/05 SFO TO DFWAA552 1/12/2006 SFO TO ORD.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              
20060118001862006011800186CE  2006       1          18         2006FA0000032    120060112G2822LW15473         PUMP                                    CESSNA172   172R        2072401CE  LYC   IO360 IO360L2A         EA                              ENGINE          LEAKING         D      K   NONE                                                                                            K  FLUID LOSS                                                                    TXTAXI/GRND HDL  1                      SW0979LU 1821                   17281163    L3087351A                   AIRCRAFT WAS PARKED FOR 3 WEEKS. FOUND FUEL/OIL MIX LEAKING FROM MUFFLER EXHAUST PIPE. FUEL LEAKED VIA GRAVITY FROM TANKS THROUGH PUMP, INTO PUMP DRIVE LEVER AREA, THEN, VIA THE ACCESSORY SECTION INTO ENGINE . FOUND ENGINE CRANK CASE FILLED WITH AVGAS.  CYLINDERS WERE ALSO FULL OF GAS/OIL MIX AND WERE HYDRAULICALLY LOCKED. FUEL/OIL MIX WAS DRAINING OUT EXHAUST VALVES INTO MUFFLER. NOTE: FUEL DID NOT DRAIN OUT OF DRAIN PORT ON FUEL PUMP. DISASSEMBLED PUMP. DRAIN PORT WAS NOT OBSTRUCTED.                                                                                                                                                                                                                                      1H71 3O3  ONT3A12    1E10                 
20060118001872006011800187CE  2006       1          18         2006FA0000033    120060112G2822LW15473         PUMP                                    CESSNA172   172R        2072401CE  LYC   IO360 IO360L2A         EA                              ENGINE          LEAKING         D      K   NONE                                                                                            K  FLUID LOSS                                                                    TXTAXI/GRND HDL  1                      SW0979LU 1821                   17281163    L3087351A                   AIRCRAFT WAS PARKED FOR 3 WEEKS. FOUND FUEL/OIL MIX LEAKING FROM MUFFLER EXHAUST PIPE. FUEL LEAKED VIA GRAVITY FROM TANKS THROUGH PUMP, INTO PUMP DRIVE LEVER AREA, THEN, VIA THE ACCESSORY SECTION INTO ENGINE . FOUND ENGINE CRANK CASE FILLED WITH AVGAS.  CYLINDERS WERE ALSO FULL OF GAS/OIL MIX AND WERE HYDRAULICALLY LOCKED. FUEL/OIL MIX WAS DRAINING OUT EXHAUST VALVES INTO MUFFLER.  NOTE: FUEL DID NOT DRAIN OUT OF DRAIN PORT ON FUEL PUMP. DISASSEMBLED PUMP. DRAIN PORT WAS NOT OBSTRUCTED.                                                                                                                                                                                                                                     1H71 3O3  ONT3A12    1E10                 
20060117003412006011700341CE  2006       1          17         2006FA0000034    120060112G7331MS3126F1065     CONNECTOR                               CESSNA441   441         2076020CE  GARRTTTPE331TPE33110    01514WP                              ZONE 400        MISMARKED       B      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      GL07                                                                    REPLACEMENT CONNECTOR FOR RT ENGINE FUEL FLOW TRANSDUCER.  INSTALLED NEW CONNECTOR AND UPON CHECKOUT FOUND THAT FUEL FLOW INDICATOR NOW OPERATES BACKWARDS.  FURTHER INVESTIGATION REVEALS THAT NEWLY INSTALLED CONNECTOR PIN HOLES ARE NOT PROPERLY MARKED.  IN FACT THE MARKINGS ON THE FRONT END OF CONNECTOR DO NOT MATCH THE MARKINGS AT THE BACK OF THE CONNECTOR.  TROUBLESHOOTING ALSO REVEALED THAT THE MISWIRING OF THE CONNECTOR HAS PERMANENTLY DAMAGED THE FUEL FLOW INDICATOR.  PROBLEM WAS RESOLVED BY ORDERING A SECOND NEW CONNECTOR FROM MFG. CHECKED TO MAKE SURE THAT THE PIN LOCATION MARKINGS WERE CORRECT.  NEW CONNECTOR INSTALLED WITH NEW FUEL FLOW INDICATOR.                                                        1L72 3T4  TRTA28CE   E4WE                 
20060117003432006011700343CE  2006       1          17         2006FA0000035    120060112G781020M911          MUFFLER                                 ZINAIRCH2000CH2000      9950100CE                                                               ENGINE          CRACKED         D      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      ININSP/MAINT     1                      GL159229 80                                                             TAILPIPE CRACKED WHERE WELDED TO CAN, CRACKED .7500 OF WAY AROUND TAILPIPE LETTING EXHUAST INTO CABIN HEAT SHROUD.  PART TOTAL TIME IN SERVE OF 80 HRS.  FOUND DURING 50 HR OIL CHANGE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L71 3O    NTTA5CH                        
20060117003422006011700342CE  2006       1          17         2006FA0000036    120060112G781020M911          MUFFLER                                 ZINAIRCH2000CH2000      9950100CE                                                               ENGINE          CRACKED         D      K   NONE                                                                                            B  SMOKE/FUMES/ODORS/SPARKS                                                      ININSP/MAINT     1                      GL159229 80                                                             TAILPIPE CRACKED WHERE WELDED TO CAN, CRACKED .7500 OF WAY AROUND TAILPIPE LETTING EXHAUST INTO CABIN HEAT SHROUD.  PART TOTAL TIME IN SERVICE OF 80 HRS.  FOUND DURING 50 HR OIL CHANGE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L71 3O    NTTA5CH                        
20060117003472006011700347CE  2006       1          17         2006FA0000037    120060112G7331MS3126F1065     CONNECTOR                               CESSNA441   441         2076020CE  GARRTTTPE331TPE33110    01514WP                              FUEL FLOW INDICAMISMARKED       B      O   OTHER                                                                                           W  INADEQUATE Q C                                                                ININSP/MAINT     1                      GL07                                                                    PURCHASED A REPLACEMENT CONNECTOR FOR THE RT ENGINE FUEL FLOW TRANSDUCER.  INSTALLED NEW CONNECTOR AND UPON CHECKOUT FOUND THAT FUEL FLOW INDICATOR NOW OPERATES BACKWARDS.  FURTHER INVESTIGATION REVEALS THAT NEWLY INSTALLED CONNECTOR PIN HOLES ARE NOT PROPERLY MARKED.  IN FACT THE MARKINGS ON THE FRONT END OF THE CONNECTOR DO NOT MATCH THE MARKINGS AT THE BACK OF THE CONNECTOR.  TROUBLESHOOTING ALSO REVEALED THAT THE MISWIRING OF THE CONNECTOR HAS PERMANENTLY DAMAGED THE FUEL FLOW INDICATOR.  PROBLEM WAS RESOLVED BY ORDERING A SECOND NEW CONNECTOR FROM MFG. CHECKED TO MAKE SURE THAT THE PIN LOCATION MARKINGS WERE CORRECT.  NEW CONNECTOR INSTALLED WITH NEW FUEL FLOW INDICATOR.                                    1L72 3T4  TRTA28CE   E4WE                 
20060117003322006011700332CE  2006       1          17         2006FA0000038    120060105G323045A3951141      UPLOCK                                  BEECH MU300 400A        1155402CE  PWA   JT15  JT15*       52060NE                              NOSE GEAR UPLOCKINTERMITTENT    E      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      GL21674SF2132                   RK232                                   AFTER TAKEOFF LANDING GEAR WAS SELECTED UP AND GEAR CAME UP TOO BUT RED WARNING LIGHT IN GEAR HANDLE STAYED ON AND YOU COULD HEAR THE DOORS WERE STILL OPEN.  SELECTED GEAR DOWN AND RETURNED TO BASE.  FOUND NOSE GEAR UPLOCK WAS INTERMITTENT.  RIGGED UPLOCK AND OPS CHECK.                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2H72 4F4  TRTA16SW   E1NE                 
20060117003312006011700331CE  2006       1          17         2006FA0000039    120060105G323045A3951141      UPLOCK                                  BEECH MU300 400A        1155402CE  PWA   JT15  JT15*       52060NE                              NOSE GEAR       OUT OF RIG      E      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      GL21674SF2132                   RK232                                   AFTER TAKEOFF LANDING GEAR WAS SELECTED UP AND GEAR CAME UP TO BUT RED WARNING LIGHT IN GEAR HANDLE STAYED ON AND YOU COULD HEAR THE DOORS WERE STILL OPEN.  SELECTED GEAR DOWN AND RETURNED TO BASE.  FOUND NOSE GEAR UPLOCK WAS INTERMITTENT.  RIGGED UP LOCK AND OPS CHECK GEAR.                                                                                                                                                                                                                                                                                                                                                                                                                                                             2H72 4F4  TRTA16SW   E1NE                 
20060214002472006021400247    2006       2          14         2006FA0000040    420060113G3416                ALTIMETER                               CESSNA206   T206H       2073303CE  LYC   O540  TIO540*     41532EA                              INSTRUMENT PANELERRATIC         G      K   NONE                                                                                            SE AFFECT SYSTEMS            VIBRATION/BUFFET                                    CRCRUISE         1                      WP231836U65                     T20608548                               AT TAKEOFF POWER (2500 RPM) AND CRUISE OVER 2390 RPM, THE STANDBY ALTIMETER MAY OSCILLATE 20 FT TO 100 FT (3500 FT CRUISE ALTITUDE).AT CRUISE, THE AUTOPILOT UNCOUPLED ITSELF THREE TIMES.DESCENT AND APPROACH (BELOW 2390 RPM) OSC. WAS 20 TO 40 FEET. BELOW 2300 RPM THE ALT. WAS STEADY.GARMIN 1000 EFIS INSTALLATION HAS THE STNBY ALTIMETER HARD MOUNTED TO A LARGE INSTRUMENT PANEL WITH NO VIBRATION DAMPENING MECHANISM. DURING CRUISE, WHEN THE ALTIMETER WAS OSCILLATING THE GREATEST, APPLYING MODERATE HAND PRESSURE (APPX. 10 LBS.) TO THE INSTRUMENT PANEL LESSENED THE AMOUNT OF OSCILLATION.THE AUTOPILOT CONTROL PANEL (HARD MOUNTED BELOW THE STANDBY ALTIMETER) CONTAINS AN ANEROID SIMILAR TO ONE IN THE STANDBY ALTIMETER. 1H71 3O3  ORTA4CE    E14EA                
20060117003402006011700340CE  2006       1          17         2006FA0000041    120060112G7331MS3126F1065     CONNECTOR                               CESSNA441   441         2076020CE  GARRTTTPE331TPE33110    01514WP                              ZONE 400        MISMARKED       B      O   OTHER                                                                                           W  INADEQUATE Q C                                                                ININSP/MAINT     1                      GL07                                                                    WE PURCHASED A REPLACEMENT CONNECTOR FOR THE RT ENGINE FUEL FLOW TRANSDUCER.  INSTALLED NEW CONNECTOR AND UPON CHECKOUT FOUND THAT FUEL FLOW INDICATOR NOW OPERATES BACKWARDS.  FURTHER INVESTIGATION REVEALS THAT NEWLY INSTALLED CONNECTOR PIN HOLES ARE NOT PROPERLY MARKED.  IN FACT THE MARKINGS ON THE FRONT END OF THE CONNECTOR DO NOT MATCH THE MARKINGS AT THE BACK OF THE CONNECTOR.  TROUBLESHOOTING ALSO REVEALED THAT THE MISWIRING OF THE CONNECTOR HAS PERMANENTLY DAMAGED THE FUEL FLOW INDICATOR.  PROBLEM WAS RESOLVED BY ORDERING A SECOND NEW CONNECTOR FROM MFG. CHECKED TO MAKE SURE THAT THE PIN LOCATION MARKINGS WERE CORRECT.  NEW CONNECTOR INSTALLED WITH NEW FUEL FLOW INDICATOR.                                 1L72 3T4  TRTA28CE   E4WE                 
20060214002292006021400229    2006       2          14         2006FA0000042    420060117G23500110040110      AUDIO PANEL                             DIAMONDA20  DA20C1      2990001GL                                                               RADIO PANEL     BURNED          B      K   NONE                                                                                            BW SMOKE/FUMES/ODORS/SPARKS  INADEQUATE Q C                                      ININSP/MAINT     1                      NE03176MA18                     C0345                                   AIRCRAFT HEADSET MICROPHONE JACKS ARE UNIQUILY WIRED FOR SENNHIESER ANR HEADSETS WITH AIRCRAFT SUPPLIED POWER FROM THE MICROPHONE JACK KEY TERMINAL. THIS IS WIRED DIFFERANTLY THAN SHOWN IN MFG GMA-340 INSTALLATION MANUAL. USE OF STANDARD AIRCRAFT HANDHELD MIC IN HEADSET JACKS CAUSED PRINTED CIRCUIT LANDS TO BURN OFF MAIN PRINTED CIRCUIT BOARD OF GMA-340 UNIT RESULTING IN A COMPLETE LOSS OF RADIO COMMUNICATIONS AND INTERCOM OPERATION. JACKS NOT PLACARDED BY MFGR AS (HEADSET MICROPHONE ONLY), OR (NO HAND MIC). ALSO, NO WARNING IN POH. EVEN IF PLACARDS WERE INSTALLED, USING A STANDARD MICROPHONE IN A STANDARD AIRCRAFT JACK, SHOULD NOT CAUSE TOTAL LOSS OF AC COMMUNICATIONS.                                          1L71 3O    NTTA4CH                        
20060214002302006021400230    2006       2          14         2006FA0000043    420060117G23500110040110      AUDIO PANEL                             DIAMONDA20  DA20C1      2990001GL                                                               RADIO PANEL     BURNED          B      K   NONE                                                                                            BW SMOKE/FUMES/ODORS/SPARKS  INADEQUATE Q C                                      ININSP/MAINT     1                      NE03176MA18                     C0345                                   AC HEADSET MICROPHONE JACKS ARE UNIQUELY WIRED FOR SENNHIESER ANR HEADSETS WITH AIRCRAFT SUPPLIED POWER FROM THE MICROPHONE JACK KEY TERMINAL. THIS IS WIRED DIFFERENTLY THAN SHOWN IN GARMIN'S GMA-340 INSTALLATION MANUAL. USE OF STANDARD AIRCRAFT HANDHELD MIC. IN HEADSET JACKS CAUSED PRINTED CIRCUIT LANDS TO BURN OFF MAIN PRINTED CIRCUIT BOARD OFN GMA-340 UNIT RESULTING IN COMPLETE LOSS OF RADIO COMMUNICATIONS AND INTERCOM OPERATION. JACKS NOT PLACARDED BY MFGR AS (HEADSET MICROPHONE ONLY), OR (NO HAND MIC). ALSO, NO WARNING IN POH. EVEN IF PLACARDS WERE INSTALLED, USING A STANDARD MICROPHONE IN A STANDARD AC JACK, SHOULD NOT CAUSE TOTAL LOSS OF AC COMMUNICATIONS.                                                 1L71 3O    NTTA4CH                        
20060214002452006021400245    2006       2          14         2006FA0000044    420060117G23500110040110      AUDIO PANEL                             DIAMONDA20  DA20C1      2990001GL                                                               RADIO PANEL     BURNED          B      K   NONE                                                                                            BW SMOKE/FUMES/ODORS/SPARKS  INADEQUATE Q C                                      UKUNKNOWN        1                      NE03176MA18                     C0345                                   AIRCRAFT HEADSET MICROPHONE JACKS ARE UNIQUILY WIRED FOR ANR HEADSETS WITH AIRCRAFT SUPPLIED POWER FROM THE MICROPHONE JACK KEY TERMINAL. THIS IS WIRED DIFFERANTLY THAN SHOWN IN MFG GMA-340 INSTALLATION MANUAL. USE OF STANDARD AIRCRAFT HANDHELD MIC IN HEADSET JACKS CAUSED PRINTED CIRCUIT LANDS TO BURN OFF MAIN PRINTED CIRCUIT BOARD OFN GMA-340 UNIT RESULTING IN COMPLETE LOSS OF RADIO COMMUNICATIONS AND INTERCOM OPERATION. JACKS NOT PLACARDED BY MFG AS (HEADSET MICROPHONE ONLY), OR (NO HAND MIC). ALSO, NO WARNING IN POH. EVEN IF PLACARDS WERE INSTALLED, USING A STANDARD MICROPHONE IN A STANDARD AIRCRAFT JACK, SHOULD NOT CAUSE TOTAL LOSS OF AIRCRAFT COMMUNICATIONS.                                                 1L71 3O    NTTA4CH                        
20060126000322006012600032SO  2006       1          26         2006FA0000045    220060118G741410357586        DISTRIBUTOR GEARTELEDYNESYSTS6LSC25     CESSNA172   R172K       2072431CE  CONT  O360  IO360KB     17025SO                              MAGNETO         FAILED          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO114718K175        D04HA269R   R1722017    288769                      ELEVEN GEAR TEETH FAILED ON NYLON DISTRIBUTOR GEAR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3O3  O  3A17    E1CE                 
20060126000912006012600091SO  2006       1          26         2006FA0000046    120060111G531012034535003     WINDOW FRAME                            EMB   120   EMB120RT    3260202SO  PWA   118   PW118            NE                              RT COCKPIT      CRACKED         B  OWFRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE05200CD26579                  120200                                  COPILOTS SIDE WINDOW LOWER STRUCTURAL BEAM IS CRACKED AT RT WINDSHIELD AFT BEAM.  NORMAL OPS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4T4  TRTA31SO   E20NE                
20060124001922006012400192SO  2006       1          24         2006FA0000047    120060111G531012034535001     WINDOW FRAME                            EMB   120   EMB120RT    3260202SO  PWA   118   PW118            NE                              LT COCKPIT      CRACKED         B  OWFRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE05196CA28588                  120196                                  PILOTS SIDE WINDOW LOWER STRUCTURAL BEAM IS CRACKED AT LEFT WINDSHIELD AFT BEAM.  NORMAL OPS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4T4  TRTA31SO   E20NE                
20060120001022006012000102SO  2006       1          20         2006FA0000050    220060110G85301864321         CYLINDER                                BEECH 58    58          1152740CE  CONT  O520  IO520CB     17032SO                              ENGINE          CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         ININSP/MAINT     1                      SO038195R                       TH529       299141R                     ENGINE CYLINDER CRACKED AND BARREL AND HEAD.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L72 3O3  O  3A16    E5CE                 
20060126000992006012600099SO  2006       1          26         2006FA0000051    220060110G85301847312         CYLINDER                                BEECH 58    58          1152740CE  CONT  O520  IO520CB     17032SO                              ENGINE          CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO038195R611                    TH529       299141R                     ENGINE CYLINDER CRACKED AT BARREL AND HEAD.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L72 3O3  O  3A16    E5CE                 
20060126000962006012600096NE  2006       1          26         2006FA0000053    220060107G8520LW13923         PISTON                                  MAULE M7    M7235       5460170SO  LYC   O540  IO540W1A5   41532NE                              ENGINE          BROKEN          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM019234N1078                   4119C       L2492048A                   INSPECTION OF THE OIL FILTER DURING ROUTINE OIL CHANGE FOUND 2 EA (.1250 INCH) DIAMETER PIECES OF ALUMINUM.  FURTHER DISASSEMBLY OF THE ENGINE/ CYLINDERS FOUND THE NR 1 CYLINDER PISTON SKIRT WAS MISSING A SECTION (.5 INCH X 1.1250 INCH LONG).  PERFORMED A DY PENETRANT INSP TO THE OTHER PISTONS.  3 WERE CRACKED AT THE SAME LOCATION.  1 HAD INDICATION OF POSSIBLE CRACK AND 1 WAS IN SERVICEABLE CONDITION.  NO OTHER DAMAGE TO THE PISTON WAS DIAMETER WAS WITHIN SERVICE LIMITS.  CYLINDER DIAMETER WAS WITHIN SERVICE LIMITS.  (K)                                                                                                                                                                                                 1H71 3O3  ONC3A23    1E4                  
20060126000862006012600086WP  2006       1          26         2006FA0000055    220060109G726130745732        CARBON SEAL                             LEAR  45    45LEAR      5170805CE  GARRTTTFE731TFE7312     01518WP                              ENGINE          WORN            D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP07411AJ747                    2011        P116515                     PERFORMED SOAP SAMPLE DUE TO FILTER BYPASSED.  SAMPLE CAME BACK NORMAL.  PERFORMED ANOTHER SOAP SAMPLE 50 HOURS LATER AND FILTER FAILED DELTA P-CHECK.  RESULTS CAME BACK (INSPECT THIS ENGINE IMMEDIATELY) INSTALLED LOANER ENGINE.  ORIGINAL ENGINE HAD NR 1, NR 3, NR 4 AND NR 5 CARBON SEALS REPLACED.  RE-INSTALLED ORIGINAL ENGINE AFTER REPAIRE.  25 HOUR SOAP SAMPLE RESULTS ARE NORMAL.  PROBABLE CAUSE IS PREMATURE WEAR/FAILURE OF CARBON SEALS.  RECOMMEND IMPROVING CARBON SEAL MATERIAL AND QUALITY. (K)                                                                                                                                                                                                                          2L72 4F4  FRTT00008WIE6WE                 
20060126001022006012600102WP  2006       1          26         2006FA0000056    220060109G726130745742        CARBON SEAL                             LEAR  45    45LEAR      5170805CE  GARRTTTFE731TFE7312     01518WP                              ENGINE          WORN            D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP07411AJ747                    2011        P116515                     PERFORMED SOAP SAMBLE DUE TO FILTER BYPASSED.  SAMPLE CAME BACK NORMAL.  PERFORMED ANOTHER SOAP SAMPLE 50 HOURS LATER AND FILTER FAILED DELTA P-CHECK.  RESULTS CAME BACK (INSPECT THIS ENGINE IMMEDIATELY).  INSTALLED LOANER ENGINE.  ORIGINAL ENGINE HAD NR1, NR3, NR4 AND NR5 CARBON SEALS REPLACED.  REINSTALLED ORIGINAL ENGINE AFTER REPAIR.  25 HOUR SOAP SAMPLE RESULTS ARE NORMAL.  PROBABLE CAUSE IS PREMATURE WEAR/FAILURE OF CARBON SEALS.  RECOMMEND IMPROVING CARBON SEAL MATERIAL AND QUALITY.  (K)                                                                                                                                                                                                                             2L72 4F4  FRTT00008WIE6WE                 
20060126001032006012600103SO  2006       1          26         2006FA0000057    120060112G57516538834         BALANCE WEIGHT                          PIPER PA28  PA28150     7102804SO  LYC   O320  O320*       41508EA                              LT AILERON      BROKEN          D  V36RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO135105W                       28122                                   REMOVED EXISTING BALANCE WEIGHT ASSEMBLY, PN 65388-34 ON THE LT AILERON AND REPLACED WITH A SERVICEABLE BALANCE WEIGHT ASSEMBLY OF THE SAME PN AND WEIGHT.  AT ANNUAL INSPECTION, THE WEIGHT WAS FOUND BROKEN OFF AT THE ATTACHMENT TUBE.  THE EXISTING RIVET PATTERN WAS REUSED.  SINCE THE WEIGHT AND ATTACHMENT POINTS WERE IDENTICAL BETWEEN THE ASSEMBLIES, THERE WAS NO CHANGE TO THE WEIGHT AND BALANCE.  THE PILOT DID NOT NOTICE ANY DIFFERENCE IN THE HANDLING OF THE RESPONSE OF THE AC PRIOR TO THE REPAIR.  THE BROKEN OFF WEIGHT WAS FOUND IN THE WING BETWEEN THE OUTER RIB AND THE ADJACENT IB RIB.  (K)                                                                                                                        1L71 3O3  O  2A13    E274                 
20060126000892006012600089NM  2006       1          26         2006FA0000058    120060102G2910                VENT LINE                               CHRIS HUSKY A1          221020XNM  LYC   O360  O360*       41514EA                              FUEL VENT       BLOCKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      AL039622V                       1154                                    BOTH LT FUEL VENT LINES BLOCKED BY ICE.  ENGINE STOPPED DURING TAXI TO RUNWAY.  ALTHOUGH PREFLIGHT LISTS CHECKING FUEL VENT LINES ARE CLEAR, THIS NEEDS TO BE EMPHASIZED MORE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3O3  ONCA22NM   E286                 
20060126000872006012600087CE  2006       1          26         2006FA0000060    120060105G5752AA50723         BUSHING                                 BEECH 58    58          1152740CE  CONT  O550  IO550*           SO                              AILERON TRIM    WORN            B  E81RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL03376W 517                    TH1970                                  AILERON TRIM MADE POPPING NOISE AS CONTROL WAS ROTATED.  FOUND BUSHING FOR CONTROL SHAFT IN PEDESTAL SEVERELY WORN ALLOWING U-JOINT TO CONTACT STRUCTURE AS CONTROL WAS ROTATED.  TRIM CABLE TENSION WAS WITHIN LIMITS, NO REASON FOR ACCELERATED WEAR NOTED.  BUSHING IS OILITE TYPE AND NO LUBRICATION IS CALLED FOR. (K)                                                                                                                                                                                                                                                                                                                                                                                                                     1L72 3O3  O  3A16    E3SO                 
20060131002112006013100211    2006       1          31         2006FA0000064    120060112G5100                CASE                                                                                                                                    UNKNOWN         LEAKING         B  JGVRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL09                                                                    IVSI WAS RECEIVED FOR REPAIR OF A CASE LEAK EXCEEDING MFG TOLERANCES.  (RC-60-VIL1) MFG ACCEPTABLE SEALANT FOR DASHPOT CYL ENDS AND FOR FEED-IN-FLANGE MNTG SCREW HEADS IS RED GLYPTAL.  5-MIN EXPOXY WAS APPLIED TO END CAPS AND FITTING FLANGE.  5-MIN EXPOXY HAS BEEN APPLIED OVER SCREW HEADS AND AROUND FITTING FLANGE THAT ATTACHES FEED-IN TUBE FROM DASHPOT ASSY TO REAR OF THE INSTRMT CASE, ALSO PACKED AROUND FEED-IN TUBE ITSELF. THIS METHOD OF SEALING WITH EXPOXY RATHER GYPTAL MAKES IT DIFFICULT TO FURTHER REPAIR THIS IVSI W/O DESTROYING DASHPOT FEED-IN TUBE.  NATURE OF EPOXY, IT DOES NOT ALLOW FLEXING AT JOINT, NOT RESPONSIVE TO CHANGE IN TEMP.  OVER TIME IT MAY PULL AWAY FROM ONE SURFACE AND ALLOW LEAKAGE.  (K)                                           
20060124001762006012400176SO  2006       1          24         2006FA0000065    120060111G531012034535001     WINDOW FRAME                            EMB   120   EMB120RT    3260202SO  PWA   118   PW118            NE                              WINDSHIELD      CRACKED         B  OWFRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE05200CD26579                  120200                                  PILOT`S SIDE WINDOW LOWER STRUCTURAL BEAM IS CRACKED AT LT WINDSHIELD AFT BEAM.  NORMAL OPERATIONS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4T4  TRTA31SO   E20NE                
20060131002202006013100220SW  2006       1          31         2006FA0000066    120060111G5320K660000         ANGLE                                   GULSTM690TP 695A        7630519SW  GARRTTTPE331TPE331*     01514WP                              FUSELAGE        MISLOCATED      D  MV5RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL117895G                       96070                                   JOGGLE IN PART NEEDS TO BE RELOCATED .2500 INCH FURTHER FROM NEAR END OF ANGLE IN ORDER TO HAVE SUFFICIENT ED TO FASTENER.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1H72 4T3  T  2A4     E2WE                 
20060131002152006013100215SW  2006       1          31         2006FA0000067    120060111G5320K6600006        ANGLE                                   GULSTM690TP 695A        7630519SW  GARRTTTPE331TPE331*     01514WP                              FUSELAGE        MISLOCATED      D  MV5RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL117896G                       96070                                   JOGGLE IN PART NEEDS TO BE RELOCATED .2500 INCH FURTHER FROM NEAR END OF ANGLE IN ORDER TO HAVE SUFFICIENT ED TO FASTENER.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1H72 4T3  T  2A4     E2WE                 
20060126001062006012600106SW  2006       1          26         2006FA0000068    120060111G5320K6600005        ANGLE                                   GULSTM690TP 695A        7630519SW  GARRTTTPE331TPE331*     01514WP                              FUSELAGE        MISLOCATED      D  MV5RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL117896G                       96070                                   JOGGLE IN PRAT NEEDS TO BE RELOCATED .2500 INCH FURTHER FROM NEAR END OF ANGLE IN ORDER TO HAVE SUFFICIENT ED TO FASTENER.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1H72 4T3  T  2A4     E2WE                 
20060126001072006012600107SW  2006       1          26         2006FA0000069    120060111G5320K6600004        ANGLE                                   GULSTM690TP 695A        7630519SW  GARRTTTPE331TPE331*     01514WP                              FUSELAGE        MISLOCATED      D  MV5RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL117896G                       96070                                   JOGGLE IN PART NEEDS TO BE RELOCATED .2500 INCH FURTHER FROM NEAR END OF ANGLE IN ORDER TO HAVE SUFFICIENT ED TO FASTENER.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1H72 4T3  T  2A4     E2WE                 
20060124001862006012400186NM  2006       1          24         2006FA0000071    120060102G321340005401        CYLINDER                                PIPER PA60  PA60601P    7106012NM                                                               MLG STRUT       CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO1591VK 4148                   61P06157963                             COLLAR SEPARATING FROM TUBE DUE TO INSUFFICIENT PENETRATION WHEN PART WAS FURNACE BRAZED OR SILVER SOLDERED TOGETHER WORKING COLLAR CAUSED PART TO WORK AND CRACK BOSS.  RECOMMEND INSPECTION OF COLLAR AT BOTTOM OF GEAR STRUT FOR ANY MOVEMENT OR WORKING BETWEEN COLLAR AND THE STRUT CYLINDER ASSY DYE CHECK WHERE PART IS MACHINED FOR CLEARANCE ON TORQUE LINKS.  (K)                                                                                                                                                                                                                                                                                                                                                                     1M72 3O    RTA17WE                        
20060126000822006012600082NE  2006       1          26         2006FA0000076    220060116G72302292260060      TURBINE WHEEL                           SNIAS 350   AS350B3     8680954EU  TMECA ARRIELARRIEL2B         NE                              GAS GENERATOR   MIGRATED        D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP23352SA           01018       3348        22396                       DURING A ROUTINE 600 HR BORESCOPE INSP OF THE GAS GENERATOR TURBINE BLADES, 2 BLADES WERE FOUND TO HAVE MOVED AFT IN THEIR (FIR-TREE) TYPE MOUNTS IN THE TURBINE DISK.  1 BLADE WAS FOUND TO HAVE MOVED .1250-.2500 INCH, AND THE OTHER LESS THAN .1250 INCH.  THE BLADES HAD TO MOVE PAST A RETAINING CLIP TO ACHIEVE THE AMOUNT OF MOVEMENT OBSERVED.  THIS TYPE OF DEFECT IS NOT LISTED AS A POSSIBLE DEFECT IN THE ENGINE MM AND SMALL AMOUNTS OF INSP REGIME.  DUE TO THE POTENTIAL EFFECTS OF THE RECOMMEND A BORESCOPE INSP OF THE BLADE ALIGNMENT BEFORE FURTHER FLIGHT AND AT AN INTERVAL OF 300 HOURS ENGINE IS BEING RETURNED TO MFG.  (K)                                                                                           1G71 3U3  U  H9EU    E00054EN             
20060126000782006012600078SO  2006       1          26         2006FA0000077    220060116G8530SA52000         CYLINDER HEAD                           BEECH 58    58          1152740CE  CONT  O520  IO520C      17032SO                              ENGINE          SEPARATED       B  WS9RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM077209B992                    TH1428      280384R                     APPEAR THAT THERE WAS A CRACK IN THE CYLINDER HEAD AT THE EXHAUST VALVE SEAT, WHICH PROPOGATED DURING OPERATION UNTIL THE CYLINDER HEAD FAILED AND SEPARATED FROM THE CYLINDER.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L72 3O3  O  3A16    E5CE                 
20060126000092006012600009CE  2006       1          26         2006FA0000078    120060103G282325CX1123AC      LEVER                                   RAYTHNDH125 HAWKER800   7450004CE  GARRTTTFE731TFE731*     01518WP                              FUEL TRANSFER   CORRODED        B  JGVRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE0971MT 8865                   258230                                  FOUND WING FUEL TRANSFER LEVER ASSY CORRODED AT FORKED END.  THIS LEVER ASSY IS NOT A DIRECT INSPECTION ITEM NOR IS IT A DIRECT LUBE ITEM.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA3EU    E6WE                 
20060130000712006013000071CE  2006       1          30         2006FA0000079    120060105G2823                LEVER                                   RAYTHNDH125 HAWKER800   7450004CE  GARRTTTFE731TFE731*     01518WP                              FUEL TRANSFER   CORRODED        B  JGVRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE0975MT 8527                   258231                                  FOUND WING FUEL TRANSFER LEVER ASSY CORRODED AT THE FORK END.  THIS LEVER ASSY IS NOT A DIRECT INSPECTION ITEM NOR IS IT A DIRECT LUBE ITEM.  (CE09200602408)  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F4  FRTA3EU    E6WE                 
20060130000722006013000072CE  2006       1          30         2006FA0000080    120060105G282325CX1123AC      LEVER                                   RAYTHNDH125 HAWKER800   7450004CE  GARRTTTFE731TFE731*     01518WP                              FUEL TRANSFER   CORRODED        B  JGVRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE09954H 5819                   258259                                  FOUND WING FUEL TRANSFER LEVER CORRODED AT BOTH ENDS.  THIS LEVER ASSY IS NOT A DIRECT INSPECTION ITEM NOR IS IT A DIRECT LUBE ITEM.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F4  FRTA3EU    E6WE                 
20060126000792006012600079CE  2006       1          26         2006FA0000081    120060108G32500543022         ROD                                     CESSNA172   172A        2072404CE  CONT  O300  O300*       17022SO                              LT STEERING     RUSTED          G      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM139852T                       47652                                   ROD END FAILED.  AIRCRAFT TURNED LT AND IMPACTED AN EMBANKMENT.  SMALL AMOUNT OF RUST ON ROD END AT THE THREADED AREA. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1H71 3O3  O  3A12    E253                 
20060130000742006013000074EU  2006       1          30         2006FA0000082    120060109G4940                SWITCH                                  HWKSLYDH125 BH125400A   4230138EU  GARRTTTFE731TFE731*     01518WP                              APU START PANEL PILOT ERROR     H      O   OTHER                                                                                           W  INADEQUATE Q C                                                                NRNOT REPORTED   1                      NM03125CK                       25266                                   PILOT MISTAKENLY TRIPPED THE APU FIRE EXTINGUISHER SWITCH INSTEAD OF THE APU START SWITCH.  BOTH SWITCHES ARE OF THE SAME STYLE, ARE LOCATED CLOSE TOGETHER AND BOTH HAVE THE SAME STYLE OF RED GUARDED SWITCHES.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4J4  F  A3EU    E6WE                 
20060131001752006013100175SW  2006       1          31         2006FA0000083    120060102G5751250000225       SKIN                                    GULSTM690TP 690B        7630516SW                                                               RT WING AILERON CORRODED        B  MV5RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL11690LL                       11544                                   CORROSION BEYOND 10 PERCENT LIMITS IN LEADING EDGE SKIN UNDER BALANCE WEIGHTS.  FOUND DURING SB238. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1H72 3T      2A4                          
20060130000752006013000075SO  2006       1          30         2006FA0000084    220060110G8530196279          CYLINDER HEAD                           BEECH 58    58          1152740CE  CONT  O520  IO520*      17032SO                              ENGINE          CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO038195R611                    TH529                                   ENGINE CYLINDER CRACKED AT BARREL AND HEAD.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L72 3O3  O  3A16    E5CE                 
20060126000472006012600047SO  2006       1          26         2006FA0000086    120060112G3244304K632         TIRE                                    EMB   135   EMB135BJ    3260306SO                                                               MLG             LEAKING         C      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL25                                                                    AFTER INSTALLING NEW TIRE ON WHEEL ASSEMBLY AND INFLATING, THE TIRE WAS DISCOVERED TO BE LEAKING AT ALL SIDEWALL WEEP HOLES.  THIS CONDITION CONTINUED EVEN AFTER THE 12 HOUR LEAK CHECK TIME HAD EXPIRED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F    RT                             
20060207002052006020700205EA  2006       2          7          2006FA0000087    220060120G7324                POPPET VALVE    LYC         63323440ASY CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              ENGINE          STICKING        B      K   NONE                                                                                            O  OTHER                                                                         TXTAXI/GRND HDL  1                      CE07575TW33   33    0A10933     172S10078   L3241851E                   AIRCRAFT WOULD NOT START. ENGINE & FUEL COLD SOAKED (JUST AT BELOW 32 DEG. F). THE FLOW DIVIDER POPPET VALVE WOULD STICK CLOSED AND PREVENT FUEL FLOW.  AFTER TROUBLSHOOTING DETERMINED THAT UNIT WOULD STICK IN  CLOSED AND OPEN POS. THE CLOSED POS. PREVENTS FUEL FLOW TO NOZZLES. FOUND IF UNIT WAS COOLED ON THE BENCH WITHOUT FUEL IN THE DIVIDER THE POPPET VALVE WOULD STILL STICK. SUSPECT MFG TOLERANCES BAD ON POPPET ASSY. TRIED DUPLICATING ON AN AIRCRAFT  1 1/2 YEARS OLDER. COULD NOT DUPLICATE. HOWEVER, COULD DUPLICATE ON AN AIRCRAFT WHO'S SERIAL NUMBER IS IN CLOSE TO THE SQUAWKED AIRCRAFT. APPEARS TO BE A SPECIFIC LOT NUMBER OF EFFECTED PARTS.  HEAT FROM RUNNING ENGINE RUNNING KEEPS VALVE MOVING FREELY.          1H71 3O3  ONT3A12    1E10                 
20060224001862006022400186CE  2006       2          24         2006FA0000088    120060124G561045AS3101011     WINDOW                                  BEECH MU300 400A        1155402CE  PWA   JT15  JT15D5      52112NE                              COCKPIT         CRACKED         E      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL21674SF2141                   RK232                                   DURING INSPECTION, THE PILOTS SIDE WINDOW WAS FOUND TO BE CRACKED THROUGH THE OUTER PANE CONNECTING 5 BOLT HOLES ALONG THE TOP OF WINDOW.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2H72 4F4  FRTA16SW   E25EA                
20060131001992006013100199CE  2006       1          31         2006FA0000090    120060106G324007515500        PLATE                                   BEECH 90    E90         1152914CE  PWA   PT6   PT6A27      52043EA                              BRAKE CYLINDER  CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL09200RE8273                   LW164                                   DURING A PHASE I AND II INSPECTION A CRACK WAS FOUND IN THIS PART ATTACHED TO THE RT GEAR ASSY.  THE CRACK IS ON THE TORQUE PLATE UPPER FORWARD BRAKE CYLINDER PIN ATTACH HOLE.  A BUSHING INSTALLED IN THIS HOLE HAS NO SIGN OF DAMAGE.  PROBABLE CAUSE OF CRACKING WOULD BE STRESS RELATED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                              1L72 3T4  T  3A20    E4EA                 
20060131001642006013100164SW  2006       1          31         2006FA0000092    120060113G7810                RISER                                   GULSTM112   114         7630314SW                                                               EXHAUST         CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP284775W207                    14105                                   TURBO SYSTEM INSTALLED IAW STL, BOTH LT AND RT EXHAUST RISERS HAD MANY CRACKS AND DEEMED UNSERVICEABLE.  207.8 HRS SINCE NEW, REPLACED UNITS FAILED IN 140.0 MORE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L71 3O      A12SO                        
20060127000692006012700069NM  2006       1          27         2006FA0000093    120060126G3231                SHEAR PIN       DORNER                  DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                                              BROKEN          E      A   UNSCHED LANDING                                                                                 E  VIBRATION/BUFFET                                                              TOTAKEOFF        1                      GL25328GT                       3183                                    CREW REPORTED DURING GEAR RETRACTION THEY HEARD AND FELT A VIBRATION FROM NOSE GEAR DOOR NOT CLOSING FULLY.  DURING INSPECTION THE RIGHT HAND FORWARD GEAR DOOR BREAKING ROD ASSEMBLY WAS FOUND TO HAVE A BROKEN SHEAR PIN.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2H72 4T4  FRTA55NM   E35NE                
20060131002062006013100206    2006       1          31         2006FA0000094    420060129G2562AK450           TRANSMITTER                             MOONEYM20   M20J        5870219SW  LYC   O360  IO360A1A    41514EA                              ELT             DETERIORATED    B  NT3RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP25201CD                       240063                                  ELT TRANSMITTER WAS REMOVED DURING ANNUAL FOR BATTERY REPLACEMENT AND TESTING. UNIT HAD BATTERIES REPLACED.  DURING TESTING THE UNIT MADE A WEAK SIGNAL OUTPUT AND HAS NO RANGE.  USED DIFFERENT SET OF BATTERIES FOR RETESTING, SAME RESULTS.  HOOKED BACK IN AIRCRAFT TO AIRCRAFT ANTENNA, TEST RESULTS THE SAME.  ARMED UNIT AND TESTED THROUGH REMOTE MOUNTED SWITCH WITH SAME UNSATISFACTORY RESULTS.  UNIT IS APPROXIMATELY 2 YEARS OLD.  TREND OF FAILURES ON THIS MAKE AND MODEL OF ELT.  SUSPECT INTERNAL DETERIORATION OF COMPONENT SECURITY.  (K)                                                                                                                                                                                    1L71 3O3  O  2A3     1E10                 
20060131001732006013100173    2006       1          31         2006FA0000096    420060117G2562                TRANSMITTER                             MOONEYM20   M20R        5870225SW  CONT  O550  IO550*           SO                              ELT             INTERMITTENT    B  NT3RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP252164K532        455647      290172                                  ELT TRANSMITTER WAS REMOVED DURING ANNUAL FOR BATTERY REPLACEMENT AND TESTING.  UPON TEST WITH BATTERIES REPLACED.  THE UNIT ON/OFF WAS INTERMITTENT AND THE REMOTE OPERATION WAS INTERMITTENT.  UNIT IS APPROXIMATELY 7 YEARS OLD.   TREND OF FAILURES ON THIS MAKE AND MODEL OF ELT.  SUSPECT INTERNAL DETERIORATION OF COMPONENT SECURITY.  (K)                                                                                                                                                                                                                                                                                                                                                                                              1L71 3O3  ORT2A3     E3SO                 
20060131001762006013100176CE  2006       1          31         2006FA0000098    120060124G3340RN24885023      LENS                                    LEAR  35    36LEAR      5170601CE  GARRTTTFE731TFE73122B   01518WP                              TAIL STROBELIGHTSPLIT           B  BHKRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA2183FN                        007                                     FAA/PMA APPROVED REPLACEMENT SPLITS/CRACKS ON INSTALL.  SHAPE IS SLIGHTLY DIFFERENT FROM PN 248850237.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F4  F  A10CE   E6WE                 
20060131001912006013100191    2006       1          31         2006FA0000099    220060123G7414BL3492901       MAGNETO                                                                                                                                 ENGINE          INOPERATIVE     B  WS9RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM07                                                                    SHOWER OF SPARKS DOESN`T WORK IAW TEST CELL.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         
20060131001672006013100167    2006       1          31         2006FA0000100    120060123G7921G05448292       OIL COOLER                                                                                                                                              CRACKED         B  WS9RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM07                                                                    CRACKED FOOT ON OIL COOLER.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          
20060131001922006013100192CE  2006       1          31         2006FA0000101    120060107G3210SM50D7          RELAY                                   BEECH 33    F33A        1151425CE  CONT  O520  IO520*      17032SO                              MLG             FAILED          B  VJ3RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP075581T                       CE1350                                  MECHANIC REMOVED NEW RELAY FROM STOCK AND INSTALLED ON AIRCRAFT AND GEAR FAILED TO EXTEND, AFTER TAPPING ON THE TOP OF RELAY GEAR WENT DOWN.  MECHANIC THEN INSTALLS ANOTHER NEW RELAY FROM STOCK AND SYSTEM OPERATED NORMAL.  PROBABLE CAUSE AT THIS TIME UNKNOWN.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L71 3O3  O  3A15    E5CE                 
20060202001222006020200122SO  2006       2          2          2006FA0000102    120060124G321040288000        TRUNNION                                PIPER PA31T PA31T       7103124SO  PWA   PT6   PT6A60A     52043NE                              RT MLG          CRACKED         E  IPMAO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP11111KV10500                  31T7920035                              DURING 100 HOUR INSPECTION FOUND CRACK IN WEB OF AFT MLG TRUNNION ASSY AIRCRAFT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L72 3T4  T  A8EA    E4EA                 
20060202001082006020200108    2006       2          2          2006FA0000103    420060109G6113C30031          PLATE                                                                                                       HARTZLHCB3T HCB3TN3     GL  SPINNER         FAILED          B  ME4RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO19                                                    BUA26690        SPINNER SUPPORT PLATES RECEIVED BROKEN WITH BOLTS STILL INSTALLED ON HUB, NO OTHER BROKEN PARTS OF THIS SUPPORT PLATE ASSY WERE FOUND ON THIS PROPELLER. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 6  CP15EA    
20060202001052006020200105SO  2006       2          2          2006FA0000104    120060121G3610J301300AR       COUPLING                                GULSTMG1159 GIV         3980115SO  RROYCETAY   TAY6118          EU                              BLEED AIR DUCT  FAILED          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA25327TL                       1339                                    WITH APU RUNNING AND BLEED AIR SELECTED ON, COUPLING FAILED CAUSING DUCT TO SEPARATE.  PROBABLE CAUSE UNKNOWN.  SUGGEST MORE AGGRESSIVE LOCKING MECHANISM.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA12EA   E25NE                
20060202001432006020200143EA  2006       2          2          2006FA0000106    220060123G7314                SEAL                                    AMTR  SKYSMISMITHMINIPLA05625N3GL  LYC   O540  TIO540J2BD  41532EA                              PUMP SHAFT      LEAKING         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL2511NS 43         HKN023FP    61P0343102  L829261A                    WITH THE ENGINE OFF AND THE FUEL BOOST PUMP ON , A STEADY STREAM OF FUEL CAME OUT THE ENGINE DRIVEN FUEL PUMP SHAFT SEAL DRAIN HOSE.  THE FUEL CONTINUED TO FLOW OUT THE DRAIN HOSE AFTER THE ENGINE WAS STARTED.  THIS IS NOT THE FIRST INSTANCE OF LEAKS WITH THIS MODEL PUMP.  THIS IS A RELATIVELY NEW DESIGN PUMP.  PUMP WAS RETURNED TO THE MFG FOR WARRANTY.  (K)                                                                                                                                                                                                                                                                                                                                                                        1B71 3O3  ONCEXPA1B71E14EA                
20060202001442006020200144EU  2006       2          2          2006FA0000107    120060120G2822568127202       PUMP                                    AIRBUS320   A320*              EU                                                               FUEL SYS        INOPERATIVE     B  G7EYO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA35                                                                    ONE FUEL PUMP WAS RETURNED FOR INSPECTION/REPAIR DUE TO A FAULT AND ASSOCIATED CB TRIP FOR LT WING TANK PUMP 2.  ONE OF TWO NUTS HOLDING THE HOUSING BERING ASSY TO THE STATOR CAP BECAME LOOSE.  THE ASSOCIATED SCREW DROPPED INTO THE STATOR WINDING, CAUSING ARCING.  THE FLAME TRAP WAS BREACHED.  DUE TO THE HOLE LEFT IN THE STATOR HOUSING BY THE MIGRATION OF THE SCREW.  THIS LEFT A DIRECT PATH TO THE FUEL.  THE MFG HAS ALSO BEEN INFORMED.  (K)                                                                                                                                                                                                                                                                                    2L72 4F    RTA46NM                        
20060202001282006020200128CE  2006       2          2          2006FA0000108    120060116G2823                CONTROL CABLE                           CESSNA182   182T        2072703CE  LYC   O540  IO540AB1A5       EA                              AFT FUEL SELECT CHAFED          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NE0338US                        18281173    L2858348                    AT AC STA 22 LWS 3 INCHES, 3.75 INCHES BELOW CABIN FLOOR, ELEVATOR TRIM CONTROL CABLES CHAFING HARD ON BOTTOM SURFACE OF .2500 DIA FUEL TUBE AT LEFT AND AFT OF AIRCRAFT FUEL SELECTOR.  IF LEFT CONTROL CABLE WILL CUT THRU FUEL TUBE  (CAUSE) NOT SEEN AT FACTORY.  REPOSITIONED FUEL TUBE UP AWAY FROM CONTROLS.  (NE03200606762) (K)                                                                                                                                                                                                                                                                                                                                                                                                        1H71 3O3  ONT3A13    1E4                  
20060202001032006020200103CE  2006       2          2          2006FA0000109    120060118G8011642087A64       ADAPTER                                 BEECH 36    A36         1151604CE  CONT  O550  IO550B           SO                              STARTER ADAPTER WRONG PART      B  MQ3RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP11268EA4                      E3473       685983                      AIRCRAFT CAME TO OUR SHOP WITH SMOKE AND OIL COMING OUT OF TAIL PIPE.  4 HOURS PRIOR, THE AIRCRAFT ANNUAL INSP WAS COMPLETED AND AT THAT TIME THE STARTER ADAPTOR WAS REPLACED WITH THE WRONG PART.  THIS AC HAD BEEN MODIFIED BY  STC WITH TORNADO ALLEY TURBO CHARGER SYS.  THE STC REQUIRED THAT STARTER ADAPTER ASSEMBLY BE CHANGED TO PN 642087A63 THAT INCLUDES A OIL SCAVENGE PUMP.  PN A2087A64 DOES NOT HAVE A SCAVENGE PUMP INSTALLED.  THE REPLACEMENT PART WAS ORDERED BY ENGINE SN NOT BY STC MODIFIED PARTS LIST.  IT WOULD BE RECOMMENDED THAT WHEN ORDERING PARTS FOR STC MODIFIED AIRCRAFT THAT THE STCC HOLDER BE CONTACTED FOR PARTS.                                                                                        1L71 3O3  O  3A15    E3SO                 
20060202001292006020200129    2006       2          2          2006FA0000110    220060123G7414BL6006061       MAGNETO                                                                                                                                 ENGINE          INOPERATIVE     B  WS9RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM07                                                                    METAL IN MAGNETO.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    
20060202001062006020200106CE  2006       2          2          2006FA0000111    120060119G3297SM50D7          RELAY                                   BEECH 33    F33A        1151425CE  CONT  O520  IO520*      17032SO                              MLG             INTERMITTENT    B  VJ3RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP075582X510                    CE1353                                  PILOT REPORTED AFTER PUTTING THE GEAR SELECTOR IN THE DOWN POSITION THE GEAR WOULDN`T EXTEND, AFTER CYCLING GEAR SELECTOR GEAR WENT DOWN, AIRCRAFT RETURNED TO BASE.  ON TROUBLESHOOTING THE MECHANIC SELECTED DOWN AND IT FAILED TO EXTEND, AFTER TAPPING ON TOP OF RELAY THE GEAR WENT DOWN.  PROBABLE CAUSE AT THIS TIME UNKNOWN.  INSTALLED NEW AND IMPROVED RELAY IAW DATE CODE.  (K)                                                                                                                                                                                                                                                                                                                                                      1L71 3O3  O  3A15    E5CE                 
20060203000852006020300085EA  2006       2          3          2006FA0000117    220060120G8520                FLANGE                                  PIPER PA28  PA28161     7102803SO  LYC   O320  O320D3G     41508EA  SNSNCH74DM  M74DM       EA  ENGINE          BROKEN          B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL21263ND                       2842064     L1016739A   A58041          BOTH FORWARD BOLT ATTACHMENT FLANGES WERE CRACKED OFF OF STARTER ATTACHMENT FLANGE ASSEMBLY. THIS CAUSED THE STARTER TO DROOP DOWNWARD WITH ONLY THE AFT BOLTS SUPPORTING THE STARTER. AS A RESULT, THE STARTER RING GEAR AND STARTER BENDIX WOULD NOT PROPERLY ENGAGE. THIS RESULTED IN THE TEETH OF THE BENDIX TO BREAK APART. THE STARTER FLANGE WAS CRACKED OFF ON BOTH THE FWD LT SIDE AND FWD RT SIDE AT A 45 DEGREE ANGLE.                                                                                                                                                                                                                                                                                                               1L71 3O3  O  2A13    E274    5  NP88614   
20060203000962006020300096EA  2006       2          3          2006FA0000118    220060130G74144302            MAGNETO                                 PIPER PA44  PA44180     7104402SO  LYC   O360  O360A1H     41514EA                                              INOPERATIVE     B      O   OTHER                                                                                           O  OTHER                                                                         ININSP/MAINT     1                      GL21295ND861                    4496030     RL74671A                    ON ENGINE INSPECTION RUN-UP MAGNETO RPM DROP NORMAL.  WHEN MECHANIC ATTEMPTED TO CHECK TIMING, FOUND TIMING 20 DEGREES LATE.  REMOVED AND DISASSEMBLED MAGNETO.  FOUND DISTRIBUTOR CARBON BRUSH MISSING AND ROTOR SHAFT BROKEN AT BASE OF SLOT FOR POINT CAM.  ALSO FOUND EXTENSIVE BURNING DAMAGE TO DISTRIBUTOR BLOCK CROSSBEAM AND ARCING DAMAGE TO COIL AND DISTRIBUTOR GEAR SHAFT.                                                                                                                                                                                                                                                                                                                                                         1L72 3O3  O  A19S0   E286                 
20060214001542006021400154CE  2006       2          14         2006FA0000119    120060130G5270631221160       SUPPORT BRACKET                         CESSNA525   525         2076601CE  WILINTFJ44  FJ44        66000GL                              DOOR            CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL09345MG1501                   5250372                                 DURING INSPECTION FOUND THE RT ATTENUATOR PIVOT SUPPORT BRACKET CRACKED.  THERE IS A SB (SB525-78-03 R1) THAT ADDRESSES THIS PROBLEM HOWEVER IT IS ONLY FOR SN PRIOR TO AND INCLUDING -0135.  HAVE BEEN FINDING THIS CONDITION ON ALL 525S EVEN IF THE SB HAS BEEN ACCOMPLISHED.  RECOMMEND THAT THE OEM REEVALUATES THIS AREA AND RE-ISSUE A SB TO CORRECT THE CONDITION.                                                                                                                                                                                                                                                                                                                                                                      1L72 4F4  FRTA1WI    E3GL                 
20060202001482006020200148CE  2006       2          2          2006FA0000121    120060110G27200025240121      ARM                                     BEECH 36    A36         1151604CE  CONT  O550  IO550*           SO                              RUDDER PEDAL    WORN            B  E81RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL033224G1719                   E2924                                   TROUBLESHOT STIFF RUDDER PEDAL STEERING AND REPLACED PILOTS RT ARM ASSY.  PN 002-524012-1 WITH NEW IAW MM.  APPEARS ARM ASSY ROLLER BEARING WAS NEVER LUBED DURING BUILD OF AIRCRAFT.  THE ROLLER BEARING WEAR CAUSED THE ARM TO SEIZE ON THE RUDDER PEDAL TORQUE TUBE AT RANDOM TRAVEL POSITIONS. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                          1L71 3O3  O  3A15    E3SO                 
20060214002352006021400235CE  2006       2          14         2006FA0000123    120060113G2800543003          MOUNT                                   CESSNA206   U206F       2073333CE  CONT  O550  IO550*           SO                              POWERPLANT      CRACKED         B  HJBRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL058419Q246                    U20603279                               DURING SCHEDULED INSPECTION FOUND THE FUEL FLOW TRANSDUCER MOUNT CRACKED COMPLETELY ACROSS ON ONE END.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1H71 3O3  O  A4CE    E3SO                 
20060214002152006021400215EU  2006       2          14         2006FA0000125    120060111G575125W181001502    AILERON                                 ISRAEL1125  ASTRASPX    4500205EU  GARRTTTFE731TFE731*     01518WP                              UPPER SURFACE   DELAMINATED     B  T77RK   NONE                                                                                            F  FLT CONT AFFECTED                                                             ININSP/MAINT     1                      GL03918MJ6061                   073                                     RT AILERON UPPER SKIN FOUND DELAMINATED FROM HONEYCOMB CORE.  DELAMINATION COVERS MORE THAN 50 PERCENT OF UPPER SURFACE.  AILERON REPLACED WITH SERVICEABLE UNIT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA16NM   E6WE                 
20060214002462006021400246EU  2006       2          14         2006FA0000126    120060126G5753T700A5755001000 FLAP                                    SOCATATBM   TBM700      8682000EU  PWA   PT6   PT6A64           EA                              IB FLAP END RIB EXCESS PLAY     D      K   NONE                                                                                            F  FLT CONT AFFECTED                                                             ININSP/MAINT     1                      EA05704QD1752                   188                                     FLAP SN SC279 WAS REMOVED FROM SERVICE FOR LOOSE ATTACHMENT INSERTS ON THE IB END RIB.  THE FLAP ATTACH CARRIAGE WAS DISCOVERED LOOSE DURING A ROUTINE DAILY PPOST FLIGHT INSPECTION, WHERE PLAY WAS NOTED BETWEEN THE FLAP ATTACH CARRIAGE AND THE IB FLAP END RIB.  IT SHOULD BE NOTED THAT ALL OPERATORS SHOULD PERFORM AN INSP IN FLAP ATTACH AREA BEFORE OPERATING AC.  (K)                                                                                                                                                                                                                                                                                                                                                                1L71 3T4  TRTA60EU   E4EA                 
20060214002232006021400223EU  2006       2          14         2006FA0000127    120060110G5754F50B134000191B3 PLATE                                   AMD   FALC50FALCON900   2700160EU  GARRTTTFE731TFE731*     01518WP                              OB SLATS        CRACKED         B  M2MRK   NONE                                                                                            F  FLT CONT AFFECTED                                                             ININSP/MAINT     1                      GL035731                        008                                     SEAL CLAMPING PLATE IS CRACKING AND BREAKING OFF AT THE 6TH AND 7TH SCREWS, (FROM IB TO OB) ON THE INSIDE OF THE OB SLATS.  SUBSEQUENT FOD DAMAGE TO THE NUT AND SAFETY WIRE OF THE BLEED AIR TUBE, AND ALSO THE LEADING EDGE OF THE WING BEHIND THE SLAT IS OCCURING DURING SLAT RETRACTION.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                              2L73 4F4  FRTA46EU   E6WE                 
20060214002242006021400224EU  2006       2          14         2006FA0000128    120060110G5754F50B144000191B3 PLATE                                   AMD   FALC50FALCON900   2700160EU  GARRTTTFE731TFE731*     01518WP                              OB SLOTS        CRACKED         B  M2MRK   NONE                                                                                            F  FLT CONT AFFECTED                                                             ININSP/MAINT     1                      GL035731                        008                                     SEAL CLAMPING PLATE IS CRACKING AND BREAKING OFF AT THE 6TH AND 7TH SCREWS, (FROM IB TO OB) ON THE INSIDE OF THE OB SLOTS.  SUBSEQUENT FOD DAMAGE TO THE NUT AND SAFETY WIRE OF THE BLEED AIR TUBE, AND ALSO THE LEADING EDGE OF THE WING BEHIND THE SLAT IS OCCURRING DURING SLAT RETRACTION.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                             2L73 4F4  FRTA46EU   E6WE                 
20060214002042006021400204SO  2006       2          14         2006FA0000129    120060125G56001159SCB51021    WINDSHIELD                              GULSTMG1159 GIV         3980115SO  RROYCETAY   TAY6118          EU                              LT              CRACKED         B  BTVRO   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      GL2349SL                        1167                                    AIRCRAFT WAS FLYING AT 41,000 FT WHEN WINDSHIELD FAILED BY OVERHEATING AND CRACKING.  PROBABLE CAUSE, HEATING ELEMENT FAILED THEN WINDSHIELD OUTER PLY FAILED.  NO RECOMMENDATION TO PREVENT FAILURE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F4  FRTA12EA   E25NE                
20060214002132006021400213CE  2006       2          14         2006FA0000132    120060130G56105111604200      WINDSHIELD                              CESSNA421   421C        2076016CE  CONT  O520  GTSIO520F   17032SO                              COCKPIT         BLEW OUT        B      BA  EMER. DESCENT           UNSCHED LANDING                                                         D  INFLIGHT SEPARATION                                                           CRCRUISE         1                      SW01     6622                   421C0426                                DURING PRESSURIZED FLIGHT, AT 17000 FEET, THE RT SIDE WINDSHIELD CRACKED AND A MAJOR PORTION BLEW OUT.  THE GLARESHIELD IS A ONE PIECE ASSY AND STAYED INTACT; THE RT SIDE REMAINED ATTACHED TO THE INSTRUMENT PANEL WHILE THE FASTENERS ON THE RT SIDE FAILED AND ALLOWED THE THAT HALF OF THE GLARESHIELD TO BE PULLED OUTSIDE.                                                                                                                                                                                                                                                                                                                                                                                                               1L72 3O3  O  A7CE    E7CE                 
20060214002362006021400236EA  2006       2          14         2006FA0000133    220060120G8510                CRANKCASE       LYC         0320D3G     PIPER PA28  PA28161     7102803SO  LYC   O320  O320D3G     41508EA  SNSNCH74DM  M74DM       EA  ENGINE          BROKEN          B      K   NONE                                                                                            S  AFFECT SYSTEMS                                                                ININSP/MAINT     1                      GL21263ND703  703   L1016739A   2842064     L1016739A   A58041          BOTH FORWARD BOLT ATTACHMENT FLANGES WERE CRACKED OFF OF STARTER ATTACHMENT FLANGE ASSEMBLY. THIS CAUSED THE STARTER TO DROOP DOWNWARD WITH ONLY THE AFT BOLTS SUPPORTING THE STARTER. AS A RESULT, THE STARTER RING GEAR AND STARTER BENDIX WOULD NOT PROPERLY ENGAGE. THIS RESULTED IN THE TEETH OF THE BENDIX TO BREAK APART. THE STARTER FLANGE WAS CRACKED OFF ON BOTH THE FWD. LT SIDE AND FWD RT SIDE AT A 45 DEGREE ANGLE.                                                                                                                                                                                                                                                                                                              1L71 3O3  O  2A13    E274    5  NP88614   
20060214001582006021400158CE  2006       2          14         2006FA0000134    120060131G7120051313211       ATTACH BRACKET                          CESSNA175   175         2072502CE  CONT  IO360 IO360*      17025CE  MCAULY2A34C D2A34C*     GL  ENGINE MOUNT    BROKEN          G      K   NONE                                                                                            O  OTHER                                                                         LDLANDING        1                      SW156612E                       56112                                   THE AC EXPERIENCED A HARD LANDING.  DURING THE LANDING THE 2 TOP ENGINE MOUNT ATTACH BRACKETS FAILED BEHIND THE FIREWALL, ALLOWING THE TOP HALF OF THE FIREWALL TO FAIL, PULLING FORWARD AND DOWN ABOUT 18 INCHES.  PN 051313211 ENGINE MOUNT ATTACH BRACKET FITS ONTO THE FRONT OF HAT CHANNELS ITEM 6 AND 7.  PN 051213211 WHICH HAS A HOLE IN IT FOR THE ENGINE MOUNT BOLT TO GO THROUGH, HAD FAILED (BROKEN IN 2 PIECES) SOME TIME AGO ON THE PILOTS TOP SIDE WITH RUST ON BOTH BRAKES.  THE BRACKET ON THE CO-PILOTS TOP SIDE HAD AN EXISTING CRACK IN THE CENTER THIRD OF IT AT THE BOLT HOLE, RUST WAS ALSO ON THIS CRACK.  (K)                                                                                                          1H71 3O3  ONT3A17    E1CE    5  CP3EA     
20060217001002006021700100NM  2006       2          17         2006FA0000135    120060130G3210NAS14635        BOLT                                    UNIVAR415   A2ALON      0540102NM  CONT  C90   C90*        17009SO                              MLG             BROKEN          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA135616F1515                   A216                                    BOLT LOCATED TOP OF SPRING OF LANDING GEAR, 3 OF THESE BOLTS HOLD THE SPRING GEAR ON.  ALL 3 BOLTS FAILED, RECOMMEND ALL 3 BOLTS IN BOTH MAIN GEAR REPLACED EACH, 1000 HRS TIME IN SERVICE.  (EA13200602813) (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L71 3O3  O  A787    E252                 
20060217001012006021700101SO  2006       2          17         2006FA0000136    120060120G36101159SB42000044  LINE                                    GULSTMG1159 GIV         3980115SO  RROYCETAY   TAY6118          EU                              PNEUMATIC SYS   CHAFED          B  CW1RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA11780E                        1165                                    DURING A ENGINE CHANGE A PYLON INSPECTION WAS BEING PERFORMED.  SPIRAL WRAP WAS NOTICED WORN.  FURTHER INVESTIGATION REVEALED CHAFF ON HIGH TEMPERATURE BLEED AIR LINE MORE THAN 50 PERCENT THROUGH.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F4  FRTA12EA   E25NE                
20060208001592006020800159CE  2006       2          8          2006FA0000138    120060202G275099100554        MOTOR                                   CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              TE FLAPS        FAILED          B  OJ2RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE07550VW                       5500307                                 THE FLAP MOTOR EXPERIENCED AN OUT OF BOX FAILURE IMMEDIATELY AFTER INSTALL.  THE MOTOR`S INTERNAL BRAKE MECHANISM MALFUNCTIONED IN A WAY TO NOT ALLOW IT TO RELEASE.  THE PART WAS IN NO WAY AIRWORTHY AND MALFUNCTION SHOULD HAVE BEEN NOTICED AT THE REPAIR STATION DURNING THE FUNCTIONAL CHECK WHICH WAS SIGNED OFF BY THEM .                                                                                                                                                                                                                                                                                                                                                                                                               1L72 4F4  F  A22CE   E1NE                 
20060214002262006021400226SO  2006       2          14         2006FA0000139    120060119G5740402915          BOLT                                    PIPER PA28  PA28R201    7102816SO  LYC   O360  IO360A1A    41514EA                              LT WING         WORN            B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL21803ND11642                  2837003                                 DURING PHASE INSPECTION LT AFT WING ATTACH BOLT WAS FOUND LOOSE. UPON FURTHER INSP IAW MFG SL 1087 THE HOLE WAS FOUND TO BE ELONGATED AND BOLT SHANK WORN.  SL 1087 DOES NOT COVER THIS SN BUT DOES COVER MODEL.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L71 3O3  O  2A13    1E10                 
20060411000292006041100029SO  2006       4          11         2006FA0000140    120060119G5740402915          ATTACH FITTING                          PIPER PA28  PA28R201    7102816SO                                                               LT WING         DAMAGED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL21803ND11642                  2837003                                 DURING PHASE INSPECTION LT AFT WING ATTACH BOLT WAS FOUND LOOSE. UPON FURTHER INSP AS PER PIPER SL 1087 THE HOLE WAS FOUND TO BE ELONGATED AND BOLT SHANK WORN. SL 1087 DOES NOT COVER THIS S/N BUT DOES COVER MODEL.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L71 3O      2A13                         
20060217000802006021700080SO  2006       2          17         2006FA0000141    220060126G73146467672A1       PUMP                                    BEECH 58    58          1152740CE  CONT  O550  IO550C           SO                              FUEL SYS        MALFUNCTIONED   D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA053214H1373                   TH1731      824463R                     FUEL PUMP FAILED AFTER LANDING.  ENGINE QUIT ON ROLL OUT.  PUMP WOULD NOT PRODUCE ENOUGH PRESSURE TO SUSTAIN AN ENGINE RPM ABOVE IDLE. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L72 3O3  O  3A16    E3SO                 
20060214002442006021400244CE  2006       2          14         2006FA0000142    120060106G280005160167        VENT LINE                               CESSNA172   172N        2072434CE  LYC   O320  O320*       41508EA                              IB RT/LT RIB    CHAFED          D      K   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      AL0373813                       17267693                                DEFECT WAS NOTED DURING SEB04-4, WHICH REQUIRED INSP OF FUEL HOSES IN OLDER PRODUCTION AC.  IN ORDER TO INSPECT ALL LINES, HEADLINER IS REQUIRED TO BE PULLED.  LINES IN QUESTION ARE LOCATED ABOVE DOORS IB OF LT AND RT FUSELAGE RIB.  PROBLEM WAS CHAFING OF FUEL VENT LINE AGAINST REAR CABIN VENT HOSE.  METAL IN CABIN HOSE RUBBED SURFACE OF FUEL VENT LINE TO PRODUCE 2 WEAR SPOTS, WHICH WHEN GENTLY PROBED WITH A SCRIBE PIERCED TUBING.  POTENTIAL FOR THIS PROBLEM TO OCCUR IS ONLY ON AC THAT HAVE DUCTING FOR REAR VENTILATION.  WEAR OF LINE COULD CAUSE FUMES TO ENTER CABIN AREA.  ACCOMPLISHMENT OF SEB04-4 TO INCLUDE CHECKING FOR POSSIBLE CHAFING OF FUEL VENT LINE AGAINST REAR CABIN VENT HOSE OR OTHER COMPONENTS.  (K) 1H71 3O3  ONT3A12    E274                 
20060214002002006021400200SO  2006       2          14         2006FA0000143    120060206G3220                CABLE           AYRES       S2RGHT65    AYRES S2    S2RHGT65    0970110SO                                                               TAIL WHEEL      BINDING         C      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      SO19                            013DC                                   AIRCRAFT TAIL WHEEL LOCKING / UNLOCKING MECHANISM NOT SATISFACTORY IAW PILOT'S REPORT. ANGLE OF CABLE AT POINT WHERE IT ATTACHES TO THE TAILWHEEL INTRODUCES BINDING. CABLE CLAMP USED DURING MANUFACTURE PINCHES END OF TELEFLEX CABLE AT MOUNTING POINT AND RESTRICTS MOVEMENT OF THE LOCK PIN ASSY. ATTENTION SHOULD BE PAID IN THE ASSEMBLY OF THE CABLE TO THE TAILWHEEL AS WELL AS IN THE DESIGN OF THE ATTACHING BRACKET ANGLES FOR PROPER CABLE RUN W/O BINDING.                                                                                                                                                                                                                                                                        1L71 3T    NC                             
20060321000372006032100037SO  2006       3          21         2006FA0000144    120060206G3220                PIN                                     AYRES S2    S2RHGT65    0970110SO                                                               TAILWHEEL LOCK  MISMANUFACTURED C      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      SO19                            013DC                                   AIRCRAFT TAIL WHEEL LOCKING / UNLOCKING MECHANISH NOT SATISFACTORY PER PILOT'S REPORT.  FOUND TAIL WHEEL LOCKING PIN OUTSIDE DIAMETER WAS NOT SUFFICIENT TO ALLOW THE LOCK PIN TO SLIDE WITHIN ITS HOUSING.  A 1/4 TURN EITHER WAY FREED THE PIN.  FURTHER, THE PART OF THE PIN THAT PROTRUDES INTO THE TAIL WHEEL CENTERING CAM WAS NOT SUFFICIENTLY ROUNDED OR TAPERED TO ALLOW A RAPID AND POSITIVE ENGAGEMENT.  THE LOCK PIN IS CRITICAL TO THE SAFE LANDING OF THE AIRCRAFT IN GUSTY WIND CONDITIONS.                                                                                                                                                                                                                                      1L71 3T    NC                             
20060216002352006021600235CE  2006       2          16         2006FA0000145    120060202G2597SPS321135       SWITCH                                  BEECH MU300 400A        1155402CE  PWA   JT15  JT15D5      52112NE                              CABIN VIP SEAT  OVERTEMP        B  UO2RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL19119QS                       RK394                                   CREW SMELLED SMOKE/ODOR IN THE CABIN DURING FLIGHT.  FOUND SLIGHT DISCOLORATION OF DUCT DUE TO AN OVERTEMP.  NO DELAMINATION NOTED AND NO OTHER SIGN OF WIRING OR COMPONENT DAMAGE.  WHILE TROUBLESHOOTING FOUND RELAY INSIDE OF VIP CABIN TEMP SWITCH PANEL THAT WAS DEFECTIVE, NOT ALLOWING COCKPIT CONTROL OF CABIN TEMP IN THE AUTO POSITION.  PILOTS HAD TO SWITCH TO MANUAL MODE TO OVERRIDE VIP TEMP SWITCH PANEL.  (K)                                                                                                                                                                                                                                                                                                                  2H72 4F4  FRTA16SW   E25EA                
20060217000102006021700010SO  2006       2          17         2006FA0000146    120060119G5512                SKIN                                    PIPER PA30  PA30        7103002SO  LYC   O320  IO320*      41508EA                              HORIZONTAL STAB BENT            G  A5ORO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO097368Y3234                   30419                                   DURING INSP OF HORIZ STAB, FWD SPAR AND CTR SECTION SKIN WAS FOUND BENT,  DISTORTED AT CENTER LIGHTENING HOLE.  SKIN AND SPAR BOTH SHOWED SIGNS OF WRINKLING AND DEFORMATION.  CLOSE INSP OF PARTS DID NOT SHOW ANY CRACKS. SPAR HAD BEEN REINFORCED WITH SPAR REINFORCEMENT AS REQUIRED BY SEB.  STAB WAS REPAIRED USING A NEW FWD SPAR ASSY WITH REINFORCEMENT NEW CTR SECTION SKIN AND COMPLYING WITH SEB.  PROBABLE CAUSE IS OVER STRESSING STAB BY FORCING TAIL DOWN TO MOVE AC ON GROUND.  RECOMMEND PERSONNEL BE BRIEFED ON PROPER PROCEDURES FOR MOVING AC, MECHANICS CLOSELY INSPECT THIS AREA FOR DAMAGE.  ALSO, RECOMMEND THAT SEB INSP OF FWD SPAR LIGHTENING HOLE AND SB INSP OF BOLT HOLES BE COMPLIED WITH AT NEXT ANNUAL INSP.  1L72 3O3  O  A1EA    1E12                 
20060216001972006021600197CE  2006       2          16         2006FA0000156    120060213G5346051313211       ATTACH BRACKET  CESSNA                  CESSNA175   175         2072502CE  CONT  O300  GO300*      17022SO                              FUSELAGE        CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE079456B2417                   55256                                   FOUND THE LT UPPER ENGINE MOUNT ATTACHMENT BRACKET CRACKED THROUGH ON THE IB SIDE. CRACK APPEARS TO HAVE ORIGINATED AT OUTER RADIUS OF WASHER THEN PROGRESSED UP AND DOWN THROUGH BRACKET. THIS INSPECTION WAS PROMPTED AFTER REPORTED FAILURE OF SAME BRACKET, SAME MAKE AND MODEL OF AIRCRAFT, THAT SUFFERED A PARTIAL ENGINE/FIREWALL SEPARATION DURING LANDING.                                                                                                                                                                                                                                                                                                                                                                             1H71 3O3  ONT3A17    E298                 
20060228000652006022800065CE  2006       2          28         2006FA0000157    120060222G5346051313211       BRACKET                                 CESSNA175   175         2072502CE                                                               ENGINE MOUNT    BENT            D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE079456B                       55256                                   A REPLACEMENT 0513132-11 ENGINE MOUNT BRACKET WAS ORDERED TO REPLACE ONE FOUND CRACKED. THE JOGGLED FLANGE WAS INCORRECTLY FORMED. THE FLANGE WAS BENT OUTWARD TO THE POINT THAT IT WOULD NOT FIT IN THE AIRCRAFT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O    NT3A17                         
20060224001802006022400180CE  2006       2          24         2006FA0000159    120060130G2170728802          WATER SEPARATOR                         CESSNA650   650         2076802CE                                                               A/C BAY         SEPARATED       B      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW05766MH                       6500015                                 EXPERIENCED AN ABRUPT CABIN PRESS FLUCTUATION DURING FLT.  FLT CREW REPORTED, ABLE TO MAINTAIN CABIN ALT WITHIN LIMITS AFTER NOTICED PROBLEM.  AFTER THIS A/C LANDED MX PERSONNEL DISCOVERED ONE OF THE ENVIRONMENTAL CONTROL SYS WATER SEPARATOR UNITS HAD SEPARATED DURING FLT.  AFFECTED WATER SEPARATOR IS MANUF WITH A CLAMP FLANGE (WHERE THE MAIN V-BAND THAT ALLOWS DISASSEMBLY OF THE UNIT FOR SERVICING IS INSTALLED) THAT IS BONDED TO FWD AND AFT SECTIONS OF UNIT.  BONDING MAT`L HAD APPARENTLY LOST ABILITY TO KEEP FLANGE ADHERED TO BODY OF UNIT ALLOWING UNIT TO SEPARATE AND CAUSE LOSS OF PRESS..                                                                                                                           2L72 4F      A9NM                         
20060228000082006022800008NM  2006       2          28         2006FA0000160    120060201G2782                GREASE FITTING  ISRAEL                  ISRAEL1125  1125               NM                                                               LE SLAT ACTUATORLEAKING         C      O   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      SW99                1820        080                                     DURING NORMAL GREASING OPERATION, THE GREASE BALL DID NOT RESET TO THE CLOSED POSITION, ALLOWING GREASE TO FLOW OUT OF THE ACTUATOR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F    RTA16NM                        
20060227002542006022700254EA  2006       2          27         2006FA0000161    220060209G7310                FUEL                                    PIPER PA28  PA28R201    7102816SO  LYC   O360  IO360C1C6   41514EA                              FUEL TANK       CONTAMINATED    B      K   NONE                                                                                            O  OTHER                                                                         UKUNKNOWN        1                      GL21384ND                       2844095     L3081251A                   BROWNISH FUEL WAS DETECTED FROM THE FUEL GASCOLATOR.  AFTER TROUBLESHOOTING IT WAS DETERMINED THAT THE BROWNISH FUEL COLOR PRESENT IN THE FUEL SYSTEM.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L71 3O3  O  2A13    1E10                 
20060227001472006022700147GL  2006       2          27         2006FA0000162    120060207G3210                PIN                                     DIAMONDA20  DA20C1      2990001GL                                                               MLG             BACKED OUT      D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM03915AF                       C0149                                   ROLL PIN LOCKING THE NOSE STRUT ELASTOMERIC SPRING PLATE (PN 20-3220-05-02) TO THE SHOCK ABSORBER ROD (PN 20-3220-05-01) HAD WORKED OUT UNLOCKING THE ASSY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L71 3O    NTTA4CH                        
20060228000322006022800032EA  2006       2          28         2006FA0000164    220060207G7421UREM40E         SPARK PLUG                              CESSNA172   172N        2072434CE  LYC   O360  O360A4M     41514EA                              ENGINE          DEFECTIVE       B  A5ORO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO096372D                       17272758                                DURING THE INSTALLATION AND OPS CHECK OF 2 NEW MAGNETOS, HARNESS AND 8 SPARK PLUGS TO CORRECT A HARD STARTING DISCREPANCY, THE ENGINE HAD A 200 TO 300 RPM MAGNETO DROP O THE LT MAGNETO.  TROBLESHOT THE IGNITION SYSTEM USING A COLD CYLINDER TESTER AND DETERMINED THAT 1 OF 8 SPARK PLUGS WAS DEFECTIVE.  SEEMS TO BE A TREND OF BAD SPARK PLUGS BEING SHIPPED BY MFG. REMOVED DEFECTIVE SPARK PLUG AND REPLACED WITH A KNOWN GOOD SPARK PLUG AND ENGINE OPS CHECKED GOOD.  SPARK PLUGS WERE REPLACED AT TIME OF MAGNETO AND HARNESS CHANGE.  ALL OF THIS BECAUSE OF POOR QUALITY CONTROL.  (K)                                                                                                                                             1H71 3O3  ONT3A12    E286                 
20060228000062006022800006GL  2006       2          28         2006FA0000165    120060214G3220PAF18220P11     BUSHING                                 DIAMONDA40  DA40        2990002GL  LYC   O360  IO360A1A    41514EA                              NLG STRUT       MISALIGNED      B  UV6SK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM07100UV454                    40405                                   THIS ADDRESSES A CONDITION OF EXCESSIVE (0.085 INCHES) CLEARANCE BETWEEN A BUSHING AT THE BOTTOM OF THE NLG SHOCK STRUT (ITEM NR 290, PN PAF18220P11, FIG .01, CH 32-20-02, IPC) AND THE SHOCK STRUT CENTER ROD (ITEM NR 210, PN D41-3223-20-33B).  THIS CLEARANCE ALLOWS THE END FITTING (ITEM NR 310) TO SLOPE APPROX.  10 DEGREES TO ONE SIDE.  THIS RESULTS IN THE BOTTOM ELASTOMERIC DONUT TAKING ON A WEDGE SHAPE AND THE SHOCK LOADS BEING TRANSMITTED OFF THE CENTERLINE OF THE NLG SHOCK STRUT.  (K)                                                                                                                                                                                                                                   1L71 3O3  ONTA47CE   1E10                 
20060228000502006022800050GL  2006       2          28         2006FA0000166    120060214G3220PAF18220P11     BUSHING                                 DIAMONDA40  DA40        2990002GL  LYC   O360  IO360A1A    41514EA                              NLG STRUT       WORN            B  UV6SO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM07834DS1963                   40034                                   REPORT ADDRESSES A CONDITION OF EXCESSIVE (0.085 INCHES) CLEARANCE BETWEEN A BUSHING AT THE BOTTOM OF THE NLG SHOCK STRUT (ITEM NR 290, PN PAF18220P11, FIG 01, CH 32-20-02, IPC) AND THE SHOCK STRUT CENTER ROD (ITEM NR 210, PN D41-3223-20-33B).  THIS CLEARANCE ALLOWS THE END FITTING  (ITEM NR 310) TO SLOPE APPROX.  10 DEGREES TO ONE SIDE.  THIS RESULTS IN THE BOTTOM ELASTOMERIC DONUT TAKING ON A WEDGE SHAPE AND THE SHOCK LOADS BEING TRANSMITTED OFF THE CENTERLINE OF THE NLG SHOCK STUT.  (K)                                                                                                                                                                                                                                  1L71 3O3  ONTA47CE   1E10                 
20060228000332006022800033EA  2006       2          28         2006FA0000167    220060203G8530751868          CYLINDER HEAD                           PIPER PA23  PA23250     7102308SO  LYC   O540  IO540C4B5   41532EA                              NR 2 CYLINDER   SEPARATED       E  GB7AO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA1362BA 8566 1752              274859                                  CYLINDER HEAD SEPARATED FROM CYLINDER FOR REASONS UNKNOWN.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L72 3O3  O  1A10    1E4                  
20060228000042006022800004CE  2006       2          28         2006FA0000168    120060216G323326900127        ACTUATOR                                CESSNA500   500CESSNA   2076602CE  PWA   JT15  JT15D1      52060NE                              NLG             LEAKING         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO11502BE                       5000195                                 HYDRAULIC LEAK AT SWITCH ACTUATOR ENTRY INTO NLG ACTUATOR AT 231 CYCLES INSTALLED AND 4224 CYCLES SOH/NEW.  DEPELETED HYDRAULIC SYSTEM ON LANDING.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L72 4F4  F  A22CE   E1NE                 
20060228000222006022800022EU  2006       2          28         2006FA0000169    120060210G8097Z00NN6024017227 ELECTRICAL BOX                          SOCATATBM   TBM700      8682000EU  PWA   PT6   PT6A64           EA  HARTZLHCE4N HCE4N3      NE  STARTER         OVERHEATED      D      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      TXTAXI/GRND HDL  1                      EA17704QD     1280              188         PCEPM0073   HH463           DURING THE START SEQUENCE WHEN THE PILOT SELECTED THE START POSITION THE STARTER WOULD NOT RESPOND.  THE PILOT COULD HEAR THE SOUND OF RELAY CONTACTS BUT THE STARTER WOULD NOT RESPOND.  THE AIRCRAFT WAS EXAMINED BY A LINE TECHNICIAN WHO REPORTED THE ELECTRICAL MASTER SMELLED OVERHEATED AND BURNED.  THE UNIT WAS REMOVED, OVERHEATING.  REPLACEMENT UNIT OF THE SAME PN WAS INSTALLED AND THE STARTER AND ELECTRICAL SYSTEM FUNCTIONED NORMALLY.  (K)                                                                                                                                                                                                                                                                                   1L71 3T4  TRTA60EU   E4EA    5  CP10NE    
20060228000052006022800005    2006       2          28         2006FA0000170    120060217G8011MZ4212          STARTER                                                                                                                                 ENGINE          SEIZED          B  WS9RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM07                                                                    STARTER SEIZED DURING START UP.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      
20060228000522006022800052    2006       2          28         2006FA0000171    120060217G8011ES6462382       STARTER                                                                                                                                 ENGINE          CONTAMINATED    B  WS9RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM07     10                                                             WAX FROM ELECTRICAL WINDING IS SEEPING THROUGH THE PLATE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            
20060228000442006022800044    2006       2          28         2006FA0000172    120060210G2420ALX9525B        ALTERNATOR                                                                                                                              ENGINE          MISMANUFACTURED B  KC2RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL03                                                                    THIS ALTERNATOR HAS 0-HOURS TIME IN SERVICE SINCE OVERHAUL ON W/O M039030.  IN PREPARING THIS UNIT FOR INSTALLATION ON AIRCRAFT, EXCESSIVE SIDE PLAY OF ROTOR SHAFT WAS NOTED.  DISASSEMBLY OF THE UNIT REVEALED THAT THE DRIVE-END BEARING BORE WAS .015 INCH OVERSIZE AND THE BEARING WAS VERY LOOSE IN THE BORE.  THIS END FRAME SHOULD HAVE BEEN REJECTED DURING THE OVERHAUL PROCESS DUE TO THE EXCESSIVE WEAR OF THE BEARING BORE.  RECOMMENDATIONS WOULD INCLUDE CLOSER INSPECTION OF THE BEARING BORE DIMENSIONS DURING THE OVERHAUL PROCESS.  THIS UNIT WILL BE RETURNED TO BE INSPECTED AND WARRANTY REPLACED BY OVERHAULER.  (K)                                                                                                                                               
20060228000412006022800041CE  2006       2          28         2006FA0000173    120060213G28200020200005A     LINE                                    BEECH 58    58          1152740CE  CONT  O550  IO550C           SO  MCAULY3AF32C3AF32C512   GL  FUEL SYS        WORN            D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA17202P 3255                   TH1875                                  THE CROSS FEED LINE PN 002-92000-51 WAS IMPROPERLY MANUFACTURED WHICH CAUSED THE RT LANDING GEAR DRIVE TUBE TO CONTACT, AND ABRADE THE LINE DURING LANDING GEAR RETRACTION.  THE ABRASION HAD PROGRESSED TO THE POINT THAT ONLY 10 PERCENT OF THE WALL THICKNESS REMAINED.  THE REPLACEMENT LINE PN HAS BEEN MANUFACTURED TO ALLOW GREATER CLEARANCE WITH THE LANDING GEAR DRIVE TUBE.  IT IS RECOMMENDED THAT THE CLEARANCE BETWEEN THE CROSS FEED LINE AND THE DRIVE TUBE BE CHECKED.  (K)                                                                                                                                                                                                                                                    1L72 3O3  O  3A16    E3SO    5  CP22EA    
20060228000312006022800031    2006       2          28         2006FA0000174    420060216G310070265421901     COMPUTER                                GULSTMGV    GV          3980116SO  RROYCEBR700 BR700710A110     NE                                              FAILED          B  VU2RO   OTHER                                                                                           G  MULTIPLE FAILURE                                                              NRNOT REPORTED   1                      GL055PG  340                    5046                                    DURING A RECENT FLIGHT DISPLAY UNITS 1,2, AND 3 BLINKED ON AND OFF.  DISPLAY UNITS 1, 2 CYCLED ON AND OFF DISPLAY UNIT 3 WAS RED X`D.  DURING THAT TIME AN AMBER (MAU 3A FAIL) MESSAGE DISPLAYED AND A BLUE (DATABASE CONFIG) MESSAGE ALSO DISPLAYED.  AFTER 5-8 SECOUNDS, ALL DISPLAY UNITS RETURNED TO NORMAL.  AFTER 10 SECONDS THE MESSAGES WENT AWAY.  THE FAULT HISTORY WAS DOWNLOADED AND SENT TO MFG.  THE NIC/PROC NR5 MODULE WAS REPLACED IAW MFG DIRECTION.  CERT CHARLIE (ASC 904) WAS INSTALLED WHICH ADDED THE AUTO REVERSION OF THE DISPLAY UNITS IN CASE OF A FAILURE OPERATOR FEELS THIS IN CONJUNCTION WITH A BAD NIC/PROC NR5 CAUSED THE BLINKING OF THE DISPLAYS.                                                           2L72 4F4  FRTA12EA   E00057EN             
20060228000092006022800009    2006       2          28         2006FA0000175    120060206G3246                WHEEL                                                                                                                                   MLG             FAILED          C      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW99                                                                    MAIN WHEEL FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       
20060228000632006022800063SW  2006       2          28         2006FA0000176    120060215G7810PFS16201        EXHAUST PORT                            MOONEYM20   M20J        5870219SW  LYC   O360  IO360A1A    41514EA                              NR 4            BROKEN          B  ZKGRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NE05799EC121                    240920                                  INSTALLED POWER FLOW SYSTEMS EXHAUST STC NR SA02871AT AT TACH TIME 4646.93, AT TACH TIME 4768.70 THE NR 4 EXHAUST PORT HAD BROKE FREE OF MUFFLER.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L71 3O3  O  2A3     1E10                 
20060228000212006022800021SO  2006       2          28         2006FA0000183    220060203G8520AEC631475       PISTON                                  BEECH 33    E33A        1151424CE  CONT  O520  IO520BA     17032SO                              ENGINE          DAMAGED         B  MW2RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL171069F                       CE230       1218098BA                   ALL 6 PISTON SKIRTS HITTING CASE.  ALL PISTON DAMAGE BEYOND REPAIR.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L71 3O3  O  3A15    E5CE                 
20060228000772006022800077GL  2006       2          28         2006FA0000185    120060215G270011169002        TORQUE TUBE                             CIRRUSSR    SR22        2130001GL  CONT  O550  IO550N      17042SO  MCAULYD3A34 D3A34C401   GL  FLT CONTROLS    WORN            D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA07150X 315                    0813        917119      030521          INSPECTED THE FLIGHT CONTROL SYS IAW SB AND FOUND FREE PLAY AT THE TORQUE TUBE/ END FITTING INTERFACE ON BOTH SIDES.  THE RT SIDE WAS MOR PRONOUNCED THAN THE LT.  MFG CONSIDERS THIS SB TO BE OPTIONAL, HOWEVER THE CONTINUED USE WITH THIS DEFECT WILL RESULT IN THE BOLT HOLWS IN THE TORQUE TUBES CONTINUING TO ELONGATE AND EXACERBATING THE PROBLEM.  AS LONG AS THIS IS CONSIDERED OPTIONAL, CUSTOMERS WON`T PAY FOR REPAIRS UNTIL IT IS DETERMINED TO BE AN AIRWORTHINESS ISSUE.  (K)                                                                                                                                                                                                                                                   1L71 3O3  ONTA00009CHE3SO    5  CP47GL    
20060228000782006022800078GL  2006       2          28         2006FA0000186    120060215G270011168002        TORQUE TUBE                             CIRRUSSR    SR22        2130001GL  CONT  O550  IO550N      17042SO  MCAULYD3A34 D3A34C401   GL  FLT CONTROLS    WORN            D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA07150X 315                    0813        917119      030521          INSPECTED THE FLIGHT CONTROL SYSTEM IAW SB AND FOUND FREE PLAY AT THE TORQUE TUBE/ END FITTING INTERFACE ON BOTH SIDES.  THE RIGHT SIDE WAS MORE PORNOUNCED THAN THE LEFT.  MFG CONSIDERS THIS SB TO BE OPTIONAL, HOWEVER THE CONTINUED USE WITH THIS DEFECT WILL RESULT IN THE BOLT HOLES IN THE TORQUE TUBES CONTINUING TO ELONGATE AND EXACERGBATING THE PROBLEM.  AS LONG AS THIS IS CONSIDERED OPTIONAL, CUSTOMER WON`T PAY FOR REPAIRS UNTIL IT IS DETERMINED TO BE AN AIRWORTHINESS ISSUE.  (K)                                                                                                                                                                                                                                          1L71 3O3  ONTA00009CHE3SO    5  CP47GL    
20060228000382006022800038EU  2006       2          28         2006FA0000187    120060221G2741                COVER                                   ISRAEL1124  1124A       4500103EU  GARRTTTFE731TFE731*     01518WP                              ACTUATOR        MISSING         B  GSPRK   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      WP05411HB           02834AA     419                                     WHILE PERFORMING A 200 HOUR INSPECTION ON THIS AIRCRAFT, THE TAIL SECTION FAIRINGS AND PANELS WERE REMOVED.  THE PITCH TRIM ACTUATOR WAS FOUND WITH THE DUST SHIELD DOWN AGAINS THE MOTOR HOUSING.  IT WAS OBVIOUS THAT THE TIE BOLT HAD BEEN REMOVED, DUST SHIELD LOWERED AND THE TIE BOLT REINSTALLED WITHOUT THE DUST SHIELD IN PLACE.  A PREVIOUS FATALITY CRASH HAS OCCURED DUE TO THE SAME INSPECTION BEING PERFORMED AND THE TIE BOLT INCORRECTLY INSTALLED.  THIS INSPECTION AND PROCEDURE SHOULD BE REMOVED FROM  GUIDE AND BEFORE SOME CAUSES THE SAME PROBLEM AGAIN.  THIS INSPECTION SHOULD ONLY BE PERFORMED BY OEM, TOO CRITICAL FOR THE FIELD.  (K)                                                                              2M72 4F4  F  A2SW    E6WE                 
20060228000422006022800042NE  2006       2          28         2006FA0000188    120060216G2820                O-RING                                  SKRSKYS76   S76A        8143006NE  ALLSN 250C  250C30S     03013GL                              FUEL DIST       CORRODED        B  Y3ARK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW03376AL                       760002                                  FOUND O-RING AREA PITTED UPON REMOVAL.  SEVERAL TUBES IN FUEL SUPPLY SYS ALSO FOUND PITTED IN O-RING AND B-NUT AREA.  NO LEAKS FOUND.  FOUND DURING ROUTINE MAINTENANCE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1G72 3U3  U  H1NE    E1GL                 
20060228000432006022800043NE  2006       2          28         2006FA0000189    120060216G2820                O-RING                                  SKRSKYS76   S76A        8143006NE  ALLSN 250C  250C30S     03013GL                              FUEL DIST       CORRODED        B  Y3ARK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW03376AL                       760002                                  FOUND O-RING AREA PITTED UPON REMOVAL.  SEVERAL TUBES IN FUEL SUPLY SYS ALSO FOUND PITTED IN O-RING AND B-NUT AREA.  NO LEAKS FOUND.  FOUND DURING ROUTINE MAINTENANCE. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1G72 3U3  U  H1NE    E1GL                 
20060228000402006022800040NE  2006       2          28         2006FA0000190    120060216G2820                O-RING                                  SKRSKYS76   S76A        8143006NE  ALLSN 250C  250C30S     03013GL                              FUEL DIST       CORRODED        B  Y3ARK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW03376AL                       760002                                  FOUND O-RING AREA PITTED UPON REMOVAL.  SEVERAL TUBES IN FUEL SUPPLY SYS ALSO FOUND PITTED IN O-RING AND B-NUT AREA.  NO LEAKS FOUND.  FOUND DURING ROUTINE MAINTENANCE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1G72 3U3  U  H1NE    E1GL                 
20060228000392006022800039NE  2006       2          28         2006FA0000191    120060216G2820                O-RING                                  SKRSKYS76   S76A        8143006NE  ALLSN 250C  250C30S     03013GL                              FUEL SYSTEM     CORRODED        D  Y3ARK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW03376AL                       760002                                  FOUND O-RING AREA PITTED UPON REMOVAL.  SEVERAL TUBES IN FUEL SUPPLY SYS ALSO FOUND PITTED IN O-RING AND B-NUT AREA.  NO LEAKS FOUND.  FOUND DURING ROUTINE MAINTENANCE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1G72 3U3  U  H1NE    E1GL                 
20060228000102006022800010CE  2006       2          28         2006FA0000192    120060209G5710S3461111        BOLT                                    CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA  MCAULY1A170 1A170E      GL  WING            DAMAGED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA25410BS49                     172S9966    23016       3220351E        DURING FIRST PHASE INSPECTION (49 HOURS SINCE NEW)FOUND LEFT WING TO UPPER STRUT BOLT HEAD DAMAGED FROM FACTORY, APPARENTLY INSTALLED WITH VISE-GRIP TYPE TOOL. NO TORQUE SEAL FOUND ON NUT. DAMAGE EXTENSIVE ENOUGH THAT TORQUE COULD NOT BE CHECKED WITH SOCKET. PHOTOS AVAILABLE. (S3461-111 REPLACES AN8-25A.)                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O3  ONT3A12    1E10    5  NP857     
20060228000112006022800011CE  2006       2          28         2006FA0000193    120060209G5710S3461111        BOLT                                    CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA  MCAULY1A170 1A170E      GL  ZONE 500        DAMAGED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA25410BS49                     172S9966    23016       3220351E        DURING FIRST PHASE INSPECTION (49 HOURS SINCE NEW)FOUND LEFT WING TO UPPER STRUT BOLT HEAD DAMAGED FROM FACTORY, APPARENTLY INSTALLED WITH VISE-GRIP TYPE TOOL. NO TORQUE SEAL FOUND ON NUT. DAMAGE EXTENSIVE ENOUGH THAT TORQUE COULD NOT BE CHECKED WITH SOCKET. PHOTOS AVAILABLE. (S3461-111 REPLACES AN8-25A.)                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O3  ONT3A12    1E10    5  NP857     
20060227002992006022700299    2006       2          27         2006FA0000194    420060205G31607018704902      POWER SUPPLY    HONEYWELL   DU870       DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              DISPLAY UNIT    FAILED          B      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      SO13402FJ9021       00077031    3147                                    HONEYWELL DU-870 EFIS DISPLAY UNIT FAILURE IN FLIGHT.  HONEYWELL PN:7014300-902.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2H72 4T4  FRTA55NM   E35NE                
20060227002572006022700257    2006       2          27         2006FA0000195    420060205G31607018704902      POWER SUPPLY    HONEYWELL   DU870       DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              DISPLAY UNIT    FAILED          B      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      SO13402FJ9021       00077031    3147                                    HONEYWELL DU-870 EFIS DISPLAY UNIT FAILURE IN FLIGHT.  HONEYWELL PN:7014300-902.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2H72 4T4  FRTA55NM   E35NE                
20060227002582006022700258    2006       2          27         2006FA0000196    420060205G31607018704902      POWER SUPPLY    HONEYWELL   DU870       DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              DISPLAY UNIT    FAILED          B      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      SO13402FJ9021       00077031    3147                                    HONEYWELL DU-870 EFIS DISPLAY UNIT FAILURE IN FLIGHT.  HONEYWELL PN:7014300-902.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2H72 4T4  FRTA55NM   E35NE                
20060227003002006022700300    2006       2          27         2006FA0000197    420060205G31607018704902      POWER SUPPLY    HONEYWELL   DU870       DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              DISPLAY UNIT    FAILED          B      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      SO13402FJ9021       00077031    3147                                    HONEYWELL DU-870 EFIS DISPLAY UNIT FAILURE IN FLIGHT.  HONEYWELL PN:7014300-902.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2H72 4T4  FRTA55NM   E35NE                
20060227003012006022700301GL  2006       2          27         2006FA0000198    120060210G2460                ELECTRICAL BOX                          CIRRUSSR    SR22        2130001GL  CONT  O550  IO550N      17042SO                              ELECTRICAL SYS  FAULTY          G      O   OTHER                                                                                           S  AFFECT SYSTEMS                                                                NRNOT REPORTED   1                      EA25                                                                    OPERATOR REPORTS THREE CASES OF UNCOMMANDED ENGINE STARTER ENGAGEMENT.  IN TWO CASES, STARTER ENGAGED WHEN THE BATTERY MASTER WAS TURNED ON.  IN THE THIRD CASE, OPERATOR STATES THAT THE SHIP'S BATTERY CAME ON LINE UNCOMMANDED AND THAT STARTER CONCURRENTLY ENGAGED UNCOMMANDED.  IN ALL THREE CASES, REPLACEMENT OF THE AIRCRAFT POWER DISTRIBUTION BOX RECTIFIED THE PROBLEM.                                                                                                                                                                                                                                                                                                                                                             1L71 3O3  ONTA00009CHE3SO                 
20060228000142006022800014    2006       2          28         2006FA0000199    420060205G31607018704902      POWER SUPPLY    HONEYWELL               DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              DISPLAY         FAILED          G      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      SO13402FJ           00077031    3147                                    DU-870 DISPLAY UNIT REFERENCE FAILED DURING FLIGHT.  THE COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2H72 4T4  FRTA55NM   E35NE                
20060228000672006022800067SO  2006       2          28         2006FA0000201    120060220G5610                WINDOW                                  PIPER PA24  PA24250     7102404SO                                                               COCKPIT         INFLT SEPARATIONG      BA  EMER. DESCENT           UNSCHED LANDING                                                         D  INFLIGHT SEPARATION                                                           CRCRUISE         1                      NM04456P                        243276                                  PILOTS SIDE WINDOW PARTIALLY POPPED OUT AT 19,000 FEET. PRESSURIZATION ISSUES RESULTED IN EMERGECY DECENT.  OPERATOR NOTIFIED KIT MANUFACTURER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L71 3O      1A15                         
20060317000482006031700048CE  2006       3          17         2006FA0000202    120060221G812020591           TURBOCHARGER                            CESSNA414   414         2075908CE  CONT  O520  TSIO520NB   17040SO                              ENGINE          DISINTEGRATED   B  J7BRO   OTHER                                                                                           O  OTHER                                                                         ININSP/MAINT     1                      SW014243C                       4140539     R20836872J                  TURBOCHARGER CAME APART INTERNALLY RESULTING IN LOSS OF MANIFOLD PRESSURE AND ENGINE METAL CONTAMINATION.  ENGINE REMOVED FROM SERVICE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L72 3O3  ORTA7CE    E8CE                 
20060317000602006031700060CE  2006       3          17         2006FA0000203    120060131G7120SB997102        TUBE                                    CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              ENGINE MOUNT    CHAFED          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP075273U                       172S9193    L3050951A                   DURING 100 HOUR/ANNUAL INSPECTION FOUND THE ENGINE OIL DIPSTICK CHAFING SLIGHTLY ON THE ENGINE MOUNT.  INSPECTED FOR DAMAGE, ONLY PROBLEM NOTED WAS PAINT WAS CHAFED.  THIS PROBLEM WAS SUPPOSED TO HAVE BEEN TAKEN CARE OF BY THE FACTORY PRIOR TO THIS SN AIRCRAFT.  ENGINE OIL FILLER TUBE TO ENGINE MOUNT CLEARANCE, WAS ISSUED TO TAKE CARE OF EARLIER SN AIRCRAFT.  THIS AIRCRAFT EVIDENTLY DID NOT GET THE CORRECT HARDWARE AT MANUFACTURER.  INSTALLED CORRECT PARTS IAW TE IPC FOR THIS SN AIRCRAFT.  (K)                                                                                                                                                                                                                              1H71 3O3  ONT3A12    1E10                 
20060317000582006031700058CE  2006       3          17         2006FA0000204    120060121G57101019800387      COVER                                   BEECH 300   300BEECH    1152930CE  PWA   PT6   PT6A60A     52043NE                              WINGS           CHAFED          B  EWGRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO056812W5952                   FA38                                    COVER IS CHAFING LOWER FWD LT AND RT WING ATTACH PORT SPART CAP AND WING SKIN.  THE COVER HAS NO ANTI-CHAFE PROTECTION.  RECOMMEND RUBBER EDGE SEAL OR FAY SEALED EDGE TO AVOID METAL TO METAL CONTACT WITH SPAR AND WING SKIN.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4T4  T  A24CE   E4EA                 
20060406002122006040600212CE  2006       4          6          2006FA0000205    120060221G30001019800388      COVER                                   BEECH 300   300BEECH    1152930CE  PWA   PT6   PT6A60A     52043NE                              WINGS           CHAFED          B  EWGRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO056812W                       FA38                                    COVER IS CHAFING LOWER FWD LT AND RT WING ATTACH POINT, SPAR CAP AND WING SKIN.  THE COVER HAS NO ANTI-CHAFE PROTECTION.  RECOMMEND RUBBER EDGE SEAL OR FAY SEALED EDGE TO AVOID METAL TO METAL CONTACT WITH SPAR AND WING SKIN.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4T4  T  A24CE   E4EA                 
20060406001782006040600178CE  2006       4          6          2006FA0000206    120060221G57201019800387      COVER                                   BEECH 300   300BEECH    1152930CE  PWA   PT6   PT6A60A     52043NE                              WINGS           CHAFED          B  EWGRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO0579TE 5991                   FA67                                    COVER IS CHAFING LOWER FWD LT AND RT WING ATTACH POINT, SPAR CAP AND WING SKIN.  THE COVER HAS NO ANTI-CHAFE PROTECTION.  RECOMMEND RUBBER EDGE SEAL OR FAY SEAL EDGE TO AVOID METAL TO METAL CONTACT WITH SPAR AND WING SKIN.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4T4  T  A24CE   E4EA                 
20060323002052006032300205CE  2006       3          23         2006FA0000207    120060221G30001019800388      COVER                                   BEECH 300   300BEECH    1152930CE  PWA   PT6   PT6A60A     52043NE                              WING            CHAFED          B  EWGRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO0579TE 5991                   FA67                                    COVER IS CHAFING LOWER FWD LT AND RT WING ATTACH POINT SPAR CAP AND WING  SKIN.  THE COVER HAS NO ANTI-CHAFE PROTECTION.  RECOMMEND RUBBER EDGE SEAL OR FAY SEAL EDGE TO AVOID METAL TO METAL CONTACT WITH SPAR AND WING SKIN.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4T4  T  A24CE   E4EA                 
20060406001852006040600185CE  2006       4          6          2006FA0000208    120060221G57201019800387      COVER                                   BEECH 300   300BEECH    1152930CE  PWA   PT6   PT6*        52043EA                              WINGS           CHAFED          B  EWGRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05103CW4080                   FA64                                    COVER IS CHAFING LWR FWD LT AND RT WING ATTACH POINT SPAR CAP AND WING SKIN.  THE COVER HAS NO ANTI-CHAFE PROTECTION.  RECOMMEND RUBBER EDGE SEAL OR FAY SEAL EDGE TO AVOID METAL TO METAL CONTACT WITH SPAR WING SKIN.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4T3  T  A24CE   E2NE                 
20060317000512006031700051CE  2006       3          17         2006FA0000209    120060221G30001019800388      COVER                                   BEECH 300   300BEECH    1152930CE  PWA   PT6   PT6*        52043EA                              WINGS           CHAFED          B  EWGRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05103CW4082                   FA64                                    COVER IS CHAFING LOWER FWD LT AND RT WING ATTACH POINT SPAR CAP AND WING SKIN.  THE COVER HAS NO ANTI-CHAFE PROTECTION.  RECOMMEND RUBBER EDGE SEAL OR FAY SEAL EDGE TO AVOID METAL TO METAL CONTACT WITH SPAR AND WING SKIN.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4T3  T  A24CE   E2NE                 
20060316001172006031600117SO  2006       3          16         2006FA0000210    120060228G3520P24029          SWITCH                                  GULSTMG1159 GIV         3980115SO  RROYCETAY   TAY6118          EU                              FUSELAGE        FAILED          D      O   OTHER                                                                                           JN WARNING INDICATION        FALSE WARNING                                       TXTAXI/GRND HDL  1                      NM09941AM1179                   1499                                    PILOTS RECEIVED PAX OXY OFF MESSAGE BEFORE TAXI OUT, INDICATING LESS THAN 50 PSI IN PASSENGER OXYGEN BOTTLE SYSTEM. VERIFIED PAX BOTTLES WERE TURNED ON AND PRESSURES WERE READING NORMAL AT BOTTLES AND COCKPIT INDICATORS. VERIFIED FLOW FROM THERAPEUTIC OXYGEN PORT AS THIS UTILIZES PASSENGER BOTTLES.  TROUBLESHOT INDICATION SYSTEM AND FOUND FAILED SWITCH, IDENTIFIER 95S4. WIRING WAS OK. SWITCH WAS REPLACED WITH NEW UNIT. INDICATION THEN NORMAL.                                                                                                                                                                                                                                                                                  2L72 4F4  FRTA12EA   E25NE                
20060404001752006040400175SO  2006       4          4          2006FA0000211    120060211G32101159H5020085    LINE                                    GULSTMGV    GULFSTREAMGV3980116SO                                                               HYDRAULIC SYS   FRAYED          C      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      EA07405LM4569 30                541                                     DUE TO IMPROPERLY POSITIONED ELBOW DURING AIRCRAFT PRODUCTION ON RT MAIN LANDING GEAR DOOR ACTUATOR, FLEX LINE WAS CONTACTING LINE DURING DOOR RETRACTION.  THE FLEX LINE DEVELOPED A HYDRAULIC LEAK WHICH IN TURN DEPLETED THE LT AIRCRAFT HYDRAULIC SYSTEM.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F    RTA12EA                        
20060404001802006040400180    2006       4          4          2006FA0000213    420060217G2562                BATTERY         ACK                     RYAN  ST3   ST3KR       7830502WP                                                               ELT             MISINSTALLED    D      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      NM01170P            032988      1566                                    DURING REPLACEMENT OF BATTERIES FROM ELT CASE, MODERATE FORCE WAS NEEDED TO REMOVE THE BOTTOM 4 BATTERIES.  THE FIT OF THE NEW BATTERIES INTO THE CASE WAS  VERY TIGHT.  AFTER CLOSING THE ELT CASE, THE ELT BECAME HOT TO THE TOUCH.  SUSPECTING  AN ELECTRICAL SHORT CIRCUIT, THE NEW BATTERIES WERE REMOVED.  UPON EXAMINING THE NEW BATTERIES JUST REMOVED, IT WAS FOUND THAT THE PROTECTIVE COVERING ON THE TERMINAL END OF THE BATTERIES WAS SCRAPED AWAY.  THIS MUST HAVE HAPPENED BY SLIDING THE BATTERIES INTO THE TIGHT CASE.  THE RELATIVE BARE SPOTS ON THE BATTERIES WOULD ACCOUNT FOR A SHORT CIRCUITING OF THE BATTERIES THAT CAUSED THE ELT TO OVERHEAT.  IT IS BELIEVED THAT THE TECHNIQUE USED TO INSERT THE BATTERIES INTO TH1L71 3R      A749                         
20060323000532006032300053CE  2006       3          23         2006FA0000214    120060308G561099143809        WINDSHIELD                              CESSNA650   650         2076802CE                                                               COCKPIT         CRACKED         B      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      CE09430SA6269                   6507041                                 PILOT'S GLASS WINDSHIELD SHOWED SIGNS OF OVERHEATING AT UPPER CENTER EDGE CAUSING COMPLETE CRACKING OF WINDSHIELD IN A SPIDER WEB FASHION.  THE WINDSHIELD REMAINED STRUCTURALLY SOUND AND THE AIRCRAFT WAS ABLE TO LAND WITHOUT INCIDENT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F      A9NM                         
20060321000362006032100036    2006       3          21         2006FA0000215    120060228G2761120611          PISTON          BOEING                                                                                                                  ACTUATOR        CRACKED         D  DM4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO19                1292                                                SUBJECT PISTON WAS RECEIVED WITH THE 2 KENY SLOTS CRACKED ON ID RADIUS.  CAUSE UNKNOWN.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              
20060413002642006041300264NM  2006       4          13         2006FA0000216    120060228G2761656952211       HOUSING                                 BOEING737   737*               NM                                                               SPOILER ACTUATORSPLIT           D  DM4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO19                                                                    HOUSING RECEIVED SPLIT OPEN IN A RADIAL DIRECTION NEAR LARGE ID, CAUSING TOTAL FAILURE OF ASSY, CAUSE UNKNOWN.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F    RTA16WE                        
20060320000302006032000030SO  2006       3          20         2006FA0000217    120060206G56101159SCB310212   WINDSHIELD                              GULSTMG1159 GIV         3980115SO  RROYCETAY   TAY6118          EU                              COPILOT WNDSHLD CRACKED         B  UO2RO   OTHER                                                                                           G  MULTIPLE FAILURE                                                              CRCRUISE         1                      GL19181CW     6058              1001                                    OUTER PLY OF CO-PILOT WINDSHIELD CRACKED IN FLIGHT.  NO LOSS OF PRESSURIZATION OCCURRED.  APPEARS HEATING ELEMENT SHORTED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA12EA   E25NE                
20060405002532006040500253GL  2006       4          5          2006FA0000219    120060210G7800DA403           RISER                                   DIAMONDA40  DA40        2990002GL  LYC   O360  IO360A1A    41514EA                              ENGINE          CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL19164DS                       40467                                   ORDERED A NEW EXHAUST RISER FOR THE NR 2 CYLINDER.  INSPECTING THE RISER BEFORE INSTALLATION WE FOUND A CRACK AT THE WELD RADIUS OF THE MOUNT FLANGE AND THE EXHAUST PIPE.  THIS MAY HAVE ACCURED FROM EXCESS HEAT DURING MANUFACTUR.  THIS THE FIRST CRACK SEEN ON NEW RISERS SEAT TO US, BUT WE HAVE HAD 2 IN SERVICE RISERS CRACKED AT 780.4 HOURS AND 2 IN SERVICE RISERS CRACKED.  (K)                                                                                                                                                                                                                                                                                                                                                     1L71 3O3  ONTA47CE   1E10                 
20060321002372006032100237    2006       3          21         2006FA0000220    420060301G3452SSD12030A       ENCODER                                 BEECH 33    35A33       1151404CE  CONT  O470  IO470*      17026SO                              COCKPIT         OUT OF ADJUST   D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM071329Z                       CD354                                   CHECKED ENCODER SYSTEM AND COULD NOT VERIFIED REPORT OF ATTITUDE ERROR.  REPLACED TRANS CAL BLIND ENCODER AS PRECAUTIONARY MEASURE.  RECERTIFY TRANSPONDER AND ENCODER IAW FAR.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L71 3O3  O  3A15    E1CE                 
20060322001402006032200140SO  2006       3          22         2006FA0000221    120060216G32308627503         DOWNLOCK                                PIPER PA44  PA44180     7104402SO  LYC   O360  O360*       41514EA                              NOSE GEAR       FAILED          D      K   NONE                                                                                            O  OTHER                                                                         LDLANDING        1                      NM092163N                       447995222                               NOSE GEAR COLLAPSE DURING ROLLOUT AFTER BRAKE APPLICATION.  PILOT HAD 3 GREEN LIGHTS.  HOOK PORTION OF DOWNLOCK PN 86275-03 FOUND CRACKED, BROKEN OFF.  FOUND BROKEN NAS 464P4-27 ALSO FOUND FAILED.  BOLT FRACTURED MID SHANK.  HEAD PORTION OF BOLT NEVER FOUND.  REMAINDER OF BOLT WITH NUT AND COTTER PIN INSTALLED FOUND STILL INSTALLED IN DRAGLINK ASSY.  UNCLEAR AS TO WHAT FAILED FIRST.  DOWNLOCK TT 8258 HRS, BOLT TT UNKNOWN.                                                                                                                                                                                                                                                                                                       1L72 3O3  O  A19S0   E286                 
20060322001452006032200145SO  2006       3          22         2006FA0000222    120060216G3230NAS464P427      BOLT                                    PIPER PA44  PA44180     7104402SO  LYC   O360  O360*       41514EA                              NLG             FAILED          D      K   NONE                                                                                            O  OTHER                                                                         LDLANDING        1                      NM092163N                       447995222                               NOSE GEAR COLLAPSED DURING ROLL OUT, AFTER BRAKE APPLICATION.  PILOT HAD 3 GREEN LIGHTS.  HOOK PORTIONOF DOWNLOCK PN 86275-03 FOUND CRACKED, BROKEN OFF.  FOUND BROKEN PIECE ON RUNWAY.  DRAGLINK BOLT PN NAS 464P4-27 ALSO FOUND FAILED.   BOLT FRACTURED MID SHANK.  HEAD PORTION OF BOLT NEVER FOUND.  REMAINDER OF BOLT WITH NUT AND COTTER PIN INSTALLED FUND STILL INSTALLED IN DRAGLINK ASSY.  UNCLEAR AS TO WHAT FAILED FIRST.  AD WAS PREVIOUSLY COMPLIED WITH.  DOWN LOCK TT 8258 HRS, BOLT TT UNKNOWN.  (K)                                                                                                                                                                                                                          1L72 3O3  O  A19S0   E286                 
20060320000802006032000080CE  2006       3          20         2006FA0000223    120060106G3411                PITOT SYSTEM                            LEAR  35    35A         5170602CE                                                               UNKNOWN         INTERMITTENT    D  H51RK   NONE                                                                                            J  WARNING INDICATION                                                            DEDESCENT        1                      NM03122JW                       217                                     ON 1/4/06 PILOT REPORTED ALTIMETER JUMPS DURING DESCENT, 300 FT, AND WARNING HORN SOUNDS.  NO OVERSPEED.  ALTIMETER SYSTEM WAS TESTED, IAW SRM AND FOUND TO BE OPERATIONAL.  NO TROUBLE NOTED.  AIRCRAFT REMAINS RVSM COMPLAINT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F      A10CE                        
20060502000022006050200002    2006       5          2          2006FA0000224    120060228G24222001012         CIRCUIT BOARD   MARATHON                                                                                                                INVERTER        INOPERATIVE     B  NE2RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE07                1108                                                RECEIVED STATIC INVERTER FOR OVERHAUL.  PRELIMINARY INSPECTION REVEALED THAT THE  PRINTED CIRCUIT BOARD (PCB) HAD BEEN MODIFIED WITH IC SOCKETS.  THE IC CHIPS WERE INSTALLED IN THE SOCKETS AND SEALED WITH A  SILICONE LIKE SUBSTANCE RATHER THAN BEING SOLDERED DIRECTLY INTO THE PCB.  JUMPER WIRE INSTALLED ON NON COMPONENT SIDE OF PCB.  POOR (COLD) SOLDER JOINTS THROUGHOUT THE PCB NO SEALANT (CONFORMAL COATING) APPLIED TO NON COMPONENT SIDE OF PCCB AFTER REWORK.  (K)                                                                                                                                                                                                                                                                                                      
20060320000182006032000018EU  2006       3          20         2006FA0000225    120060227G2121125021116       BLOWER MOTOR                            GROB  120   G120A       1660208EU  LYC   O540  AEIO540D4D5      EA                              AC SYSTEM       WORN            B  VJ3RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP07865AF                       85005       RL2631948A                  PILOT REPORTED EXCESSIVE VIBRATION WITH AIR CONDITION ON.  WHILE TECH WAS TROUBLESHOOTING SYSTEM FOUND THAT BLOWER MOTOR HAD TOO MUCH END PLAY ON BLOWER FAN SHAFT MAKING IT VIBRATE.  NO RECOMMENDATIONS AT THIS TIME.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L71 3O3  ORTA49CE   1E4                  
20060320000112006032000011SO  2006       3          20         2006FA0000226    120060128G56101159SCB31029    WINDSHIELD                              GULSTMG1159 G1159A      3970109SO  RROYCESPEY  SPEY511*    54523EU                              PILOT WINDSHIELDBROKEN          B  VZGRK   NONE                                                                                            O  OTHER                                                                         CRCRUISE         1                      SW0599PD 5415                   314                                     AT FL 380 PILOTS WINDSHIELD SHATTERED.  SHATTERED AT HEATING ELEMENT. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F4  F  A12EA   E2EU                 
20060502000092006050200009    2006       5          2          2006FA0000227    120060222G2434ALU1003         HOUSING                                                                                                                                 ALTERNATOR      WORN            B  KC2RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03                F123155                                             THIS ALTERNATOR HAS 0 HRS TIME IN SERVICE.  DURING INSPECTION OF THIS UNIT.  IT WAS DISCOVERED THAT THE DRIVE-END BEARING BORE WAS .006, OVERSIZE AND THE BEARING WAS VERY LOOSE IN THE BEARING BORE.  THIS END FRAME SHOULD HAVE BEEN REJECTED DURING THE OVERHAUL PROCEDED DUE TO THE EXCESSIVE WEAR OF THE BEARING BORE.  THIS SAME DEFECT WAS NOTED ON 2 OF THE LAST 3 UNITS RECEIVED.  RECOMMENDATION INCLUDE A CLOSER INSPECTION FOR WEAR OF THE DRIVE END BEARING BORE SINCE THIS IS A FREQUENT PROBLEM WITH THIS MODEL. (K)                                                                                                                                                                                                                                                       
20060502000102006050200010    2006       5          2          2006FA0000228    120060302G2434ALU1003         HOUSING                                                                                                                                 ALTERNATOR      OUT OF TOLERANCEB  KC2RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03                F123149                                             THIS ALTERNATOR HAS 0 HOURS.  DURING INSPECTIONOF THIS UNIT PRIOR TO INSTALLING ON AIRCRAFT, IT WAS DISCOVERED THAT THE ROTOR HAD EXCESSIVE SIDE PLAY AND WAS ALLOWING THE ROTOR TO RUB AGAINST THE STATOR LAMINATIONS.  THE DRIVE END BEARING BORE HAS EXCESSIVE WEAR AND THE BEARING IS LOOSE IN THE BORE.  THIS CONDITION WOUD HAE RESULTED IN ALTERNATOR FAILURE AND POSSIBLY RESULTED IN ENGINE FAILURE SINCE THIS UNIT IS GEAR DRIVEN BY THE ENGINE.  THIS IS THE 3RD UNIT IN 3 WEEKS FROM THIS SUPPLIER THAT HAD THIS SAME PROBLEM.  RETURNED FOR EVALUATION AND WARRANTY REPLACEMENT.  (K)                                                                                                                                                                                        
20060321002292006032100229SO  2006       3          21         2006FA0000230    120060223G32216705403         TRUNNION                                PIPER PA32  PA32R300    7103213SO  LYC   O540  IO540K1G5   41532EA                              NOSE GEAR       CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO33196SQ3921                   32R7780259                              UPON INSPECTION OF THE NOSE GEAR.  A 4.5 INCH CRACK WAS FOUND IN THE TUBULAR AREA OF THE LANDING GEAR TRUNNION CAUSE IS UNKNOWN, BUT SUSPECT HARD LANDING OR NOSE WHEEL TURNED BEYOND LIMITS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L71 3O3  O  A3SO    1E4                  
20060321001532006032100153SW  2006       3          21         2006FA0000231    120060227G53022050318211P     FITTING                                 BELL  204   UH1H        1181407SW  ALLSN 250C  250C20B     03013GL                              TAILBOOM        FRACTURED       D      K   NONE                                                                                            E  VIBRATION/BUFFET                                                              ININSP/MAINT     1                      NM13623PB           BBBD1521    6413689                                 AC LANDED FOR SHUTDOWN AFTER OPERATING FOR APPROX 3 FLIGHT HOURS, AC WAS SHAKING DURING SHUTDOWN.  DURING POST FLIGHT INSP IT WAS FOUND THAT UPPER LT MOUNT HARD POINT PN 2050318211P ON TAILBOOM (PN 20503280071), WAS FRACTURED, HAD TORN THRU FWD TAILBOOM BLKHD (PN 205030807123S) ON AIRFRAME WAS ALSO CRACKED IN 2 PLACES RADIATING FROM BOOM MOUNT HOLE TO EDGE OF FITTING.  AC RECORDS DO NOT REFLECT ANY INSTANCE OF HARD LANDING, OVER TORQUE, OR OTHER DAMAGE HISTORY.  AC HAS APPROX 8400 HOURS TT, RECORDS SHOW THAT TAILBOOM WAS INSTALLED APPROX 5000 HOURS AGO.  SUSPECTED, WHEN UPPER FITTING FAILED INSIDE TAILBOOM, BOOM ASSY SAGGED, PLACING EXCESSIVE TWIST ON LWR LT AIRFRAME MOUNT CAUSING IT TO CRACK IN 2 PLACES.  (K) 1G71 4U3  U  EXPA1G71E4CE                 
20060321001292006032100129CE  2006       3          21         2006FA0000232    120060223G213010138402831     SWITCH                                  BEECH B300  B300        1159232CE  PWA   PT6   PT6A6       52043EA                              CABIN           OUT OF TOLERANCEB  E81RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03100BE                       FL403                                   DURING INITIAL 12 MONTH TEST OF CABIN ALTITUDE WARNING SYS FOUND BAROMETRIC SWITCH OPERATING OUT OF SPECIFIED MM TOLERANCE.  REPLACED SWITCH WITH NEW SUPERSEDING (PN 101-38402845) SWITCH ASSY FROM STOCK, NEW SWITCH ALSO TESTED OUT OF SERVICE LIMITS.  REPLACED WITH NEW (PN 101384028-45 SWITCH SUPPLIED BY RAPID, TESTS PASSED SUCCESSFULLY.  SUSPECT NEW 101-384028-31 AND 101-384028-45 SWITCH ASSY MAY HAVE FAULT WHICH CAUSES THEM TO PASS INITIAL QA TESTS, BUT FAILED AFTER USE OR IN STORAGE.  (K)                                                                                                                                                                                                                                 2L72 4T3  TRTA24CE   E4EA                 
20060321001162006032100116CE  2006       3          21         2006FA0000233    120060224G352010138402829     SWITCH                                  BEECH B300  B300        1159232CE  PWA   PT6   PT6A6       52043EA                              CABIN           OUT OF TOLERANCEB  E81RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03100BE468                    FL403                                   DURING INITIAL 12 MONTH TEST OF CABIN OXYGEN SYSTEM FOUND BAROMETRIC SWITCH OPERATING OUT OF SPECIFIED MM TOLERANCE.  REPLACED WITH NEW SUPERSEDING PN 10138402843 SWITCH SUPPLIED BY RAPID, TESTS PASSED SUCCESSFULLY.  SUSPECT NEW 101384028-29 SEITCH ASSY MAY HAVE FAULT WHICH CAUSES THEM TO PASS INITIAL QA TESTS BUT FAIL AFTER USE OR IN STORAGE.  (K)                                                                                                                                                                                                                                                                                                                                                                                  2L72 4T3  TRTA24CE   E4EA                 
20060321002332006032100233    2006       3          21         2006FA0000234    420060220G22156226717104      SERVO                                   BEECH MU300 400A        1155402CE                                                               RUDDER SERVO    INTERMITTENT    B  E81RK   NONE                                                                                            F  FLT CONT AFFECTED                                                             ININSP/MAINT     1                      GL03467LX                       RK447                                   INVESTIGATED PILOT REPORT OF INTERMITTENT RUDDER BOOST FAILURE ALONG WITH SIMULATANEOUS AUTOPILOT AND YAW DAMPER DISEGAGEMENT.  FOUND RUDDER SERVO INTERMITTENTLY FAILING.  REPLACED RUDDER SERVO WITH OVERHAULED UNIT, RUDDER BOOST AND AUTOPILOT FUNCTIONAL TESTS SATISFACTORY.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                          2H72 4F    RTA16SW                        
20060321001192006032100119NE  2006       3          21         2006FA0000235    220060215G7200                ENGINE                                  AMD   FALC50FALCON50MYST2730106EU  GARRTTTFE731TFE73140    29001NE                              FUSELAGE        UNKNOWN         B  UO2RE   ENGINE SHUTDOWN                                                                                 BJ SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION                                  CRCRUISE         1                      GL1923FM 3127 1811              296         115241                      OIL TEMP 112, OIL PSI 50, MASTER CAUTION LIGHT CAME ON OIL SMELL IN CABIN.  SHUT NR 3 ENGINE DOWN LANDED AT AIRPORT.  CAUSE UNKNOWN AT THIS TIME REMOVE ENGINE FOR INSPECTION AND REPAIR, INSTALLED RENTAL.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L73 4F4  F  A46EU   E1NM                 
20060321002342006032100234    2006       3          21         2006FA0000236    420060227G346070000006000     FLIGHT DIR                              CIRRUSSR    SR22        2130001GL  CONT  O550  IO550*           SO                              COCKPIT         INTERMITTENT    C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL1356FS                        0576                                    JUST GOT 2003 SR22 BACK FROM GETTING REVISION 6 COMPLETED.  PUT ABOUT 10 HOURS ON THE AIRPLANE.  TWICE DURING THIS TRIP, THE PFD DISPLAY ROTATED OR ROLLED LIKE THE OLD TELEVISION SETS DID.  ONCE FOR ONLY 2 OR 3 SECONDS AND ANOTHER TIME FOR MAYBE 10 TO 20 SECONDS.  BOTH OF THESE OCCURRED IN LIGHT TO ODERATE CHOP AND AFTER MORE THAN AN HOUR OF FLIGHT.  ONE OF THESE OCCURRENCES WAS IN SOLID INSTRUMENT CONDITIONS AND THE OTHER WHILE ON IFR FLIGHT, WAS IN THE CLEAR.  HE IS A PILOT FOR A MAJOR AIRLINE.  HIS OPINION WAS THAT THERE COULD BE A WIRE OR CONNECTION LOOSE INSIDE THE BOX.  (K)                                                                                                                                      1L71 3O3  ONTA00009CHE3SO                 
20060321002282006032100228SW  2006       3          21         2006FA0000237    120060217G2800212040122101    DEBRIS MONITOR                          BELL  212   212         1181420SW  PWA   PT6T  PT6T3       52045EA                              SCAVENGE CUP    DEBONDED        E  CUCAK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP17911KW1147                   30592                                   AFTER REMOVAL OF DEBRIS MONITOR FOR 50 HR, CLEAN AND INSP, THE SCAVENGE CUP/SCREEN TUBE ASSY (PN A8858 IS UNSCREWED FROM UNIT.  THE O-RING FLANGE RING GLUED ONTO SCREEN TUBE SHEARS OFF OF SCREEN GLUE LINE, AND STAYS IN THE MAIN UNIT.  FIX MAYBE TO APPLY GLUE TO RUFFED SURFACES (NOT DONE APARENTLY) AN TO INSIDE STEP OF ORING FLANGE RING TO THROUGH TUBE ASSY,OR OTHER METHOD.  (K)                                                                                                                                                                                                                                                                                                                                                    1G71 4U4  U  H4SW    E22EA                
20060321002312006032100231EA  2006       3          21         2006FA0000238    120060225G3200                LANDING GEAR                            BLANCA1413  14132       1201004EA  FRNKLN6A41656A4165*     27025EA                              WINGS           FAULTY          D      K   NONE                                                                                            O  OTHER                                                                         LDLANDING        1                      WP0774212                       1325                                    THIS LANDING GEAR RETRACTED AT TOUCH-DOWN.  AIRCRAFT WAS IN STORAGE FOR A NUMBER OF YEARS.  IT WAS PUT BACK IN SERVICE THE SUMMER OF 2005.  THE LANDING GEAR WAS OVERHAULED (MECHANICAL) IN JAN 2006.  THE GEAR WAS MODIFIED FROM HAND CRANK RETRACT TO ELE/HYD RETRACT, QUITE SOME TIME BACK.  FEEL THE ELECTRICAL PART OF THE DESIGN SHOULD BE LOOKED AT.  (NO SQUAT SWITCH, ETC) GOOD GROUND SYS IN WOOD AIRCRAFT.  (K)                                                                                                                                                                                                                                                                                                                      1L71 3O3  O  A773    E238                 
20060322001002006032200100SO  2006       3          22         2006FA0000239    220060315G8550                RELIEF VALVE                            CIRRUSSR    SR22        2130001GL  CONT  O550  IO550*           SO                              ENGINE OIL SYS  RESTRICTED      B  CTURK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL21216N 34                     1801        689051                      LOSS OF OIL PRESSURE, INSPECTED OIL PRESSURE RELIEF VAVLE AND FOUND TIP OF DRILL BIT LODGED IN RELIEF VALVE.  REMOVED TIP OF DRILL BIT AND REASSEMBLED RELIEF VALVE.  GROUND RAN, OPS CHECKED GOOD.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L71 3O3  ONTA00009CHE3SO                 
20060322001022006032200102    2006       3          22         2006FA0000240    420060208G2565D31591478       SLIDE                                   BOEING737   737300      1384610NM  CFMINTCFM56 CFM563C1    13802EU                              FUSELAGE        OUT OF ALIGNMENTB  I6XRO   OTHER                                                                                           O  OTHER                                                                         ININSP/MAINT     1                      GL11389UA                       24664                                   THE ESCAPE SLIDE FOR DOOR R-2 WAS DEPLOYED FOR A SAMPLE INSPECTION.  THE SLIDE DID NOT DEPLOY CORRECTLY, THE SLIDE INFLATED TO THE FULL LENGTH, STRAIGHT OUT FROM THE AIRCRAFT, HOWEVER, IT WAS ROTATED 90 DEGREES, AND DID NOT TOUCH THE FLOOR.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F4  FRTA16WE   E21EU                
20060322001032006032200103EA  2006       3          22         2006FA0000241    220060313G7420M2917           HARNESS                                 CESSNA172   172N        2072434CE  LYC   O320  O320H2AD    41508EA                              SPARK PLUG CAPS MISMANUFACTURED D      O   OTHER                                                                                           O  OTHER                                                                         ININSP/MAINT     1                      SO065228E                       17271783                                THE AIRCRAFT HAD MAGNETO LEADS THAT NEEDED TO BE REPLACED.  A NEW HARNESS SET WAS RECEIVED AND WAS INSTALLED ON THE ENGINE.  THE ENGINE RAN POORLY.  FOUND (T-4).  ALSO NOTED THAT THE SHIELD ON NR 1 BOTTOM WIRE HAD BEEN CUT DURING MANUFACTURER AND THE SHIELD WAS OPEN.  MFG REPLACED THE HARNESS FREE OF CHARGE AND FREIGHT FREE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                     1H71 3O3  ONT3A12    E274                 
20060322001382006032200138CE  2006       3          22         2006FA0000242    120060216G3240                LINE                                    CESSNA525   525A        2076615CE  WILINTFJ44  FJ44        66000GL                              LT MLG BRAKE    FAILED          C      K   NONE                                                                                            K  FLUID LOSS                                                                    LDLANDING        1                      SO35701TF                       525A0112    126045                      AIRCRAFT DEPARTED THE RUNWAY DURING LANDING ROLLOUT.  FAILURE OF BOTH THE HYDRAULIC AND PNEUMATIC LINES TO THE LT MAIN LANDING GEAR BRAKE CAUSED THE AIRCRAFT TO SPIN INTO A GRASSY AREA ADJACENT TO THE RUNWAY.  THE NOSE LANDING GEAR SHEARED OFF AND THE AIRCRAFT CAME TO REST ON THE MAIN LANDING GEAR AND NOSE OF THE AIRCRAFT.  THERE IS SUBSTANTIAL DAMAGE TO THE NOSE OF THE AIRCRAFT AND SOME MINOR DAMAGE TO THE WINGS.  CAUSE OF THE LINE FAILURE IS UNDER INVESTIGATION.  (SO35200603622)                                                                                                                                                                                                                                           1L71 4F4  FRTA1WI    E3GL                 
20060322001502006032200150SW  2006       3          22         2006FA0000243    120060207G3230                ACTUATOR                                GULSTM114   114TC       0145002SW  LYC   O540  TIO540*     41532EA                              NLG             UNKNOWN         B  CB5YK   NONE                                                                                            O  OTHER                                                                         LDLANDING        1                      EA35115TB                       20031       L1061461A                   AFTER REFITMENT, NLG FAILED TO EXTEND TO LAND POSITION.  AC HAD BEEN UNDERGOING WORK TO SATISFY AD.  AFTER WORK, GREEN NOSE WHEEL INDICATOR WOULD NOT ILLUM.  FLYBY OF TWR, NLG WAS PARTIALLY EXTENDED TO ANGLE OF 45 DEGREES.  RECYCLING STILL FAILED TO EXTEND NLG BEYOND 45 DEGREES. PWROFF LANDING WAS EXECUTED, NLG COLLAPSED, AC CAME TO REST ON 2 PROP BLADES, NOSE WHEEL BAY DOORS. LANDING HAD PUSHED NLG BACK TOWARD RETRACTED POSITION BUT WITH PART OF TIRE PROTRUDING THROUGH PARTIALLY OPEN NOSE BAY DOORS.  PIN ATTACHING  NOSE GEAR ACTUATOR TO NOSE LEG WAS REMOVED.  GEAR FELL UNHINDERED AND UNAIDED TO DOWNLOCKED POSITION.  INSP OF NLG, WHEN NG ACTUATOR IS AVAILABLE, (SHAFT BENT 45 DEGREES IN ACCIDENT) .  (K)         1L71 3O3  ORTA12SO   E14EA                
20060322002602006032200260CE  2006       3          22         2006FA0000244    120060210G5753052390138       FLAP                                    CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA  MCAULY1A170 1A170E      GL  WINGS           CRACKED         B  NM2RK   NONE                                                                                            F  FLT CONT AFFECTED                                                             ININSP/MAINT     1                      GL193533U1200                   172S8890    L2982051A   UK23072         AIRCRAFT CAME IN FOR AN ANNUAL INSPECTION, DAMAGE TO THE FLAPS WERE FOUND DURING ROUTINE INSPECTION PROCESS.  RT FLAP HAD CRACKS RADIATING OUT FROM RIVETS ON LOWER T/E SKIN, PLUS CRACKS RADIATING OUT FROM L/E SKIN, ON BOTTOM OF FLAP, IB OF MOUNTING BRACKET.  DAMAGE DESCRIBED WAS ON RT FLAP.  LT FLAP HAD SAME DAMAGE, ONLY LESS SEVERE.  THE PROBABLE CAUSE WAS SUSPECTED TO BE CAUSED FROM LOWERING THE FLAPS AT TOO HIGH AN AIRSPEED.  FLIGHT DEPARTMENT CHAIRMAN AGREED TO DISCUSS THIS POSSIBLE PROBLEM WITH THE OTHER FLIGHT INSTRUCTORS, SO THEYY CAN DISCUSS THE PROBLEM WITH THEIR STUDENTS.  (K)                                                                                                                               1H71 3O3  ONT3A12    1E10    5  NP857     
20060323000422006032300042EA  2006       3          23         2006FA0000245    220060218G7200                ENGINE                                  DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A27      52043EA                              LT WING         MAKING METAL    C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP1972GC                        264         PCE41557                    LT ENGINE OIL PRESSURE STARTED FLUCTUATING.  PILOT RETURNED TO AIRPORT.  MAINTENANCE CHECKED OIL FILTER AND FOUND METAL IN OIL.  ENGINE REMOVED AND SENT TO REPAIR FACILITY.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1H72 3T4  TRTA9EA    E4EA                 
20060323001632006032300163EU  2006       3          23         2006FA0000246    120060221G5740T700A5760031020 ATTACH BRACKET                          SOCATATBM   TBM700      8682000EU  PWA   PT6   PT6A64           EA                              OB LT WING      CRACKED         C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA05703QD5659                   129                                     DURING A ROUTINE PHASE INSPECTION, THE LT WING TIP ASSY WAS REMOVED TO FACILITATE FURTHER INSPECTION OF THE AILERON CABLE.  AFTER REMOVAL OF THE TIP, THE INSPECTING TECHNICIAN NOTICED A CRACK IN AT THE OB ATTACH POINT.  THE BRACKET WAS REMOVED AND INSPECTED WITH A 20X MAGNIFYING GLASS WHICH REVEALED NO LESS THAN 6 CRACKS IN THE BRACKET.  IT IS RECOMMENDED THAT ALL LT AND RT ATTACH BRACKETS BE INSPECTED FOR CRACKS WITH THE WING TIPS REMOVED.  (K)                                                                                                                                                                                                                                                                               1L71 3T4  TRTA60EU   E4EA                 
20060323000502006032300050EU  2006       3          23         2006FA0000247    120060221G5740T700A5760031000 SUPPORT BRACKET                         SOCATATBM   TBM700      8682000EU  PWA   PT6   PT6A64           EA                              AILERON         CRACKED         C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA05701QD5954                   126                                     DURING A 6000 HOUR INSPECTION, THE LT AND RT WING TIP ASSEMBLIES WERE REMOVED TO FACILITATE FURTHER INSPECTION OF THE AILERON SYSTEM.  AFTER REMOVAL OF THE TIPS THE INSPECTING TECHNICIAN NOTED CRACKS IN BOTH THE LT AND RT AILERON OB ATTACH POINTS.  THE BRACKET WAS REMOVED AND INSPECTED WITH A 10X MAGNIFYING GLASS WHICH CONFIRMED CRACKS IN BOTH THE BRACKETS.  IT IS RECOMMENDED THAT ALL LT AND RT ATTACH BRACKETS BE INSPECTED FOR CRACKS WITH THE WING TIPS REMOVED.  LT BRACKET (PN T700A5760031000) RT BRACKET (PN T700A5760031001)                                                                                                                                                                                              1L71 3T4  TRTA60EU   E4EA                 
20060323001642006032300164EU  2006       3          23         2006FA0000248    120060221G5740T700A5760031001 ATTACH BRACKET                          SOCATATBM   TBM700      8682000EU  PWA   PT6   PT6A64           EA                              OB WING ASSY    CRACKED         C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA05701QD                       126                                     DURING A 6000 HOUR INSPECTION, THE LT AND RT WING TIP ASSEMBLIES WERE REMOVED TO FACILITATE FURTHER INSPECTION OF THE AILERON SYSTEM.  AFTER REMOVAL OF THE TIPS THE INSPECTING TECHNICIAN NOTED CRACKS IN BOTH THE LT AND RT AILERON OB ATTACH POINTS.  THE BRACKET WAS REMOVED AND INSPECTED WITH A 10X MAGNIFYING GLASS WHICH CONFIRMED CRACKS IN BOTH THE BRACKETS.  IT IS RECOMMENDED THAT ALL LT AND RT ATTACH BRACKETS BE INSPECTED FOR CRACK WITH THE WING TIPS REMOVED.  LT BRACKET (PN T700A5760031000) ( RT BRACKET (PN T700A5760031001) (K)                                                                                                                                                                                         1L71 3T4  TRTA60EU   E4EA                 
20060406002112006040600211CE  2006       4          6          2006FA0000249    120060215G3510553008          GASKET                                  LEAR  55    55LEAR      5170702CE  GARRTTTFE731TFE7313A    01518WP                              O2 MASK         LEAKING         B  OVVRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA1132KJ            8953        93                                      PILOT O2 MASK HAD ORIGINAL O/H DATE OF 6/05.  MASK WAS PLACED IN SERVICE IN AC 55093.  MASK DID NOT TEST PROPERLY AT DELIVERY DATE OF 6/23/05.  MASK WAS SENT BACK, FOUND TO HAVE A LEAK.  MASK WAS REPAIRED AND SENT BACK TO AC.  MASK WAS FOUND TO BE LEAKING AGAIN AFTER 2 WEEKS IN AIRCRAFT.  AGAIN, IT WAS REPAIRED.  PLACED BACK IN SERVICE, AFTER 2 MONTHS MASK WAS FOUND LEAKING AGAIN.  IT WAS SENT BACK FOR ANOTHER REPAIR, DATED 12/5/05.  MASK HAS BEEN FOUND TO BE LEAKING FOR FOURTH TIME, SENT BACK FOR FOURTH TIME FOR REPAIR.  4 REPAIRS ON THIS MASK SINCE O/H DATE OF 6/05 IS UNACCEPTABLE.  HAVE SERIOUS DOUBTS AS TO CAPABILITIES TO MAKE OVERHAULS AND REPAIRS THAT LAST.  PILOT O2 MASK IS VERY CRITICAL COMPONENT.      2L72 4F4  F  A10CE   E6WE                 
20060323000432006032300043CE  2006       3          23         2006FA0000250    120060222G5346051313211       BRACKET         CESSNA                  CESSNA175   175         2072502CE  CONT  O300  GO300*      17022SO                              ENGINE COMPARTMTCRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE077362M2268                   55662                                   INSP 0513132-11, MOUNT BRACKET WAS FOUND TO BE CRACKED. CRACK RAN VERT THROUGH BRACKET AROUND OUTER RADIUS OF AN960-616 WASHER ON UPPER ENG MOUNT BOLT. INSP WAS DONE DUE TO 2 OTHER KNOWN REPORTS OF CRACKS IN THIS BRACKET ON SAME MODEL OF AC, ONE RESULTED IN A PARTIAL ENG AND FIREWALL SEPARATION FROM AC ON LANDING.  MUST LOOK INSIDE STRINGER BEHIND  INSTRUMENT PANEL. RECOMMEND THAT SPECIAL ATTENTION BE PAID TO UPPER ENG MOUNT BRACKETS DURING INSP.  0513132-3 AND -4 STRINGER ASSEMBLIES WERE USED ON 175 SN 55001 THRU 17557119, 172 SN 17247747 THRU 17272884P172 SN P17257120 THRU P17257188 F172 SN F17201235 THRU F17201909  FR172 SN FR172-0001 THRU FR17200655R172 SN R1722000 THRU R1723199.                            1H71 3O3  ONT3A17    E298                 
20060512000442006051200044CE  2006       5          12         2006FA0000251    120060222G3010SMR20142112     BOOT                                    BEECH 90    B90         1152912CE                                                               WINGS           MISLOCATED      B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM03379VM                       LW27                                    UPON INSTALLATION OF NEW LT AND RT WING DE-ICE BOOTS WITH NEW PMA P/N SMR2014-21-1, AND -2, IT WAS DISCOVERED THE AIR INLET TUBES ARE INSTALLED IN THE WRONG LOCATION, MAKING IT IMPOSSIBLE TO MATCH THE BOOT CENTERLINE WITH THE LE CENTERLINE.  MFG AND OEM DRAWINGS SHOW 1 INCH FROM BOOT CENTERLINE TO INLET TUBE CENTERLINE.  SMR BOOTS HAVE 1.5625 INCH.  THE ONLY WAY THIS BOOT CAN BE INSTALLED IS TO SHIFT THE ENTIRE BOOT UP ON THE WING AT LEAST .5625 INCH.  THIS CAUSES CONCERN FOR CHANGE IN STALLING SPEED AT SLOW FLIGHT WITH THE BOOTS INFLATED.  SMR HAS BEEN VERY HELPFUL AND CONCERNED.  OEM BOOTS WERE PURCHASED AND INSTALLED.  SMR BOOTS WERE RETURNED.                                                                  1L72 3T      3A20                         
20060512000572006051200057CE  2006       5          12         2006FA0000252    120060222G3010SMR20142112     BOOT                                    BEECH 90    B90         1152912CE                                                               WINGS           MISMANUFACTURED B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM03379VM                       LW27                                    ON INSTALLATION OF NEW LT AND RT WING DE-ICE BOOTS, PMA P/N SMR2014-21-1,  -2, WAS DISCOVERED AIR INLET TUBES ARE INSTALLED IN WRONG LOCATION, MAKING IT IMPOSSIBLE TO MATCH BOOT CENTERLINE WITH LE CENTERLINE.  OEM DRAWINGS SHOW 1 INCH FROM BOOT CENTERLINE TO INLET TUBE CENTERLINE.  SMR BOOTS HAVE 1.5625 INCH.  ONLY WAY THIS BOOT CAN BE INSTALLED IS TO SHIFT ENTIRE BOOT UP ON WING AT LEAST .5626 INCH.  CAUSES CONCERN FOR CHANGE IN STALLING SPEED AT SLOW FLIGHT WITH BOOTS INFLATED.  SMR HAS SOLD APPROX 20 UNITS WITH NO COMPLAINTS.  SEVERAL MECHANICS  (THAT IS JUST REF LINE ON BOOT, GO AHEAD AND GLUE THEM ON).  SMR HAS BEEN VERY HELPFUL AND CONCERNED.  OEM BOOTS WERE PURCHASED, INSTALLED.  SMR BOOTS WERE RETURNED.1L72 3T      3A20                         
20060323000542006032300054SO  2006       3          23         2006FA0000253    120060217G8000                WIRE            PIPER                   PIPER PA28  PA28161     7102803SO  LYC   O320  O320D3G     41508EA  SNSNCH74D   74DM        EA  CONTACTOR       LOOSE           B      H   DEACTIVATE SYST/CIRCUITS                                                                        B  SMOKE/FUMES/ODORS/SPARKS                                                      ININSP/MAINT     1                      SO159206H                       2841006     L1229139A   A53071          MFG HAS RECENTLY ISSUED REPLACEMENT PWR CONTACTORS, IN THIS CASE FOR ENG STARTER, WITH CONTACTORS THAT HAVE PLASTIC INSULATED MOUNTING (FEET). REPLACEMENT CONTACTORS UTILIZE A GROUND WIRE UNDER BOLT HEAD OF ONE OF MOUNT BOLTS FOR CONTACTOR ACTIVATION CIRCUIT GROUND. PLASTIC PORTION OF FEET COMPRESS DURING INSTALLATION, TORQUE PROCESS. CONTACTOR ATTACH POINT LOOSENS CAUSING CIRCUIT WIRE TO GROUND, TO LOOSEN RESULTING IN HIGH RESISTANCE TO GROUND FOR STARTER CONTACTOR ACTIVATION CIRCUIT. RESULT, PLASTIC (FEET) MELT DUE TO HIGH RESISTANCE HEAT, CAUSING MATERIAL ON CABIN SIDE OF FIREWALL TO CAUSE SMOKE IN COCKPIT.  BELIEVE THAT THIS COULD CAUSE A FIRE.                                                                1L71 3O3  O  2A13    E274    5  NP88614   
20060323002012006032300201CE  2006       3          23         2006FA0000254    120060223G5511                SPAR                                    LEAR  55    55LEAR      5170702CE  GARRTTTFE731TFE731*     01518WP                              STABILIZER      CORRODED        C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO17355RM                       033                                     INSPECTIONS, HAVE FOUND SERIOUS EXFOLIATION CORROSION IN THE REAR SPAR FLANGES, NEAR THE ELEVATOR HINGE BRACKETS OF AT LEAST 2 AIRCRAFT. CORROSION HAD PROGRESSED TO THE EXTENT REQUIRING REMOVAL/REPLACEMENT OF THE SPAR FLANGES OR REPLACEMENT OF THE STABILIZER.  RECOMMEND A MORE DETAILED INSPECTION OF THE SPAR FLANGES AND A CONSIDERABLE SHORTENING OF THE TIME BETWEEN INSPECTION REQUIREMENTS. THE CORROSION HAD PROGRESSED TO THE POINT OF COMPROMISING THE INTERIORITY OF THE SPAR AND ATTACHED ELEVATOR HINGE MOUNTING.                                                                                                                                                                                                            2L72 4F4  F  A10CE   E6WE                 
20060323000672006032300067CE  2006       3          23         2006FA0000255    120060223G5511                SPAR                                    LEAR  55    55LEAR      5170702CE  GARRTTTFE731TFE731*     01518WP                              STABILIZER      CORRODED        C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO17355RM                       033                                     DURING 12,000/12 YR DEMATE INSPECTIONS WE HAVE FOUND SERIOUS EXFOLIATION CORROSION IN THE REAR SPAR FLANGES, NEAR THE ELEVATOR HING BRACKETS OF AT LEAST TWO AIRCRAFT. CORROSION HAD PROGRESSED TO THE EXTENT REQUIRING REMOVAL/REPLACEMENT OF THE SPAR FLANGES OR REPLACEMENT OF THE STABALIZER.I RECOMMEND A MORE DETAILED INSPECTION OF THE SPAR FLANGES AND A CONSIDERABLE SHORTENING OF THE TIME BETWEEN INSPECTION REQUIREMENTS. IN MY OPINION, THE CORROSION HAD PROGRESSED TO THE POINT OF COMPROMISING THE INTERURITY OF THE SPAR AND ATTACHED ELEVATOR HING. MOUNTING.                                                                                                                                                                2L72 4F4  F  A10CE   E6WE                 
20060323002022006032300202CE  2006       3          23         2006FA0000256    120060223G5511                SPAR                                    LEAR  55    55LEAR      5170702CE                                                               STABILIZER      CORRODED        C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO17355RM                       033                                     INSPECTIONS HAVE FOUND SERIOUS EXFOLIATION CORROSION IN THE REAR SPAR FLANGES, NEAR THE ELEVATOR HINGE BRACKETS OF AT LEAST 2 AIRCRAFT. CORROSION HAD PROGRESSED TO THE EXTENT REQUIRING REMOVAL/REPLACEMENT OF THE SPAR FLANGES OR REPLACEMENT OF THE STABILIZER.  RECOMMEND A MORE DETAILED INSPECTION OF THE SPAR FLANGES AND A CONSIDERABLE SHORTENING OF THE TIME BETWEEN INSPECTION REQUIREMENTS. IN MY OPINION, THE CORROSION HAD PROGRESSED TO THE POINT OF COMPROMISING THE SPAR AND ATTACHED ELEVATOR HINGE MOUNTING.                                                                                                                                                                                                                 2L72 4F      A10CE                        
20060323001182006032300118    2006       3          23         2006FA0000257    420060303G2211065001767904    AUTOPILOT SYS                           CESSNA182   182T        2072703CE                                                                               INTERMITTENT    B  FSERO   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      NE05                                                                    INTERMITTENT PITCH TRIM AND ACCELEROMETER FAILURES.  POSSIBLY CAUSED BY INADEQUATE CONNECTOR ENGAGEMENT WITH THE MOUNTING RACK CONNECTORS, CAUSED BY IMPROPER POSITIONING OF THE TOP COVER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1H71 3O    NT3A13                         
20060323001322006032300132CE  2006       3          23         2006FA0000258    120060301G2700                FLT CONTROLS                            CESSNA172   172M        2072418CE                                                                               SEIZED          C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL001295U                       17266989                                AIRCRAFT HAD BEEN TREATED WITH ACF-50 OVER THE LIFE OF THE AIRFRAME.  SEVERAL PULLEYS IN THE AILERON, ELEVATOR AND FLAP SYSTEMS WERE FOUND SEIZED OR GUMMED UP WITH ACF-50.  LAST APPLICATION OF ACF-50; 18MO.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H71 3O    NT3A12                         
20060405002252006040500225CE  2006       4          5          2006FA0000259    120060307G27102424000258      CASTING                                 LEAR  60    60LEAR      5170707CE  PWA   305   PW305            NE                              LT AILERON      BENT            B  JGVRK   NONE                                                                                            F  FLT CONT AFFECTED                                                             ININSP/MAINT     1                      CE09647TS                       047                                     INCOMING INSPECTION FOUND AILERON DRIVE YOKE ATTACH CASTING BENT.  UPON FURTHER INSPECTION IT WAS DISCOVERED THE DRIVE YOKE UPPER OR LOWER SHIMS WERE NOT INSTALLED.  DRIVE YOKE ATTACH BOLT WAS INSTALLED CAUSING THE CASTING TO BE BENT AND REQUIRES REPLACEMENT BY OEM.  THIS COULD HAVE BEEN PREVENTED BY FOLLOWING MAINTENANCE MANUAL INSTALLATION INSTRUCTIONS.  (K)                                                                                                                                                                                                                                                                                                                                                                      2L72 4F4  FRTA10CE   E35NE                
20060404002382006040400238CE  2006       4          4          2006FA0000260    120060306G79218406R           OIL COOLER                              CESSNA172   172M        2072418CE  LYC   O360  O360A1A     41514EA                                              SPLIT           C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM015496H                       17265466    L2971136A                   DURING ROUTINE RUN-UP FOLLOWING AN OIL CHANGE, AN IMMEDIATE EXPULSION OF SEVERAL QUARTS OF OIL OCCURRED IN SECONDS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1H71 3O3  ONT3A12    E286                 
20060404002372006040400237CE  2006       4          4          2006FA0000262    120060301G2810PMA20331        FUEL CELL                               BEECH 95    95B55       1152729CE  CONT  O470  IO470*      17026SO                              LT, RT WINGS    DETERIORATED    D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW0556JK 2814 1778  690         TC1938                                  FOUND FUEL SYTEM CONTAMINATED WITH AN UNKNOWN SUBSTANCE.  AFTER HAVING THE ENTIRE SYSTEM DRAINED, FLUSHED AND THE ENGINE FUEL INJECTION SYSTEM OVERHAULED, THE AIRCRAFT WAS REFUELED AND FLOWN.  AFTER A SHORT FLIGHT, THE SUMPS WERE CHECKED AGAIN AND THE SUBSTANCE WAS FOUND AGAIN.  BOTH FORWARD FUEL CELLS WERE REMOVED FROM THE AIRCRAFT.  THE SPONGE-LIKE MATERIAL INSIDE THE WING ROOT HEADER TANK PORTION OF THE FUEL CELL WAS FOUND IN A DETERIORATED CONDITION AND CONTAMINATING THE ENTIRE FUEL SYSTEM. NEW FUEL CELLS WERE ORDERED.  (K)                                                                                                                                                                                           1L72 3O3  ORT3A16    E1CE                 
20060405001532006040500153CE  2006       4          5          2006FA0000265    120060301G2810PMA20332        BAFFLE                                  BEECH 95    95B55       1152729CE  CONT  O470  IO470*      17026SO                              WING FUEL CELLS DETERIORATED    D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW0556JK 2814 1778  692         TC1938                                  FOUND FUEL SYSTEM CONTAMINATED WITH AN UNKNOWN SUBSTANCE.  AFTER HAVE THE ENTIRE SYSTEM DRAINED, FLUSHED AND THE ENGINE FUEL INJECTION SYSTEM OVERHAULED, THE AIRCRAFT WAS REFUELED AND FLOWN.  AFTER A SHORT FLIGHT, THE SUMPS WERE CHECKED AGAIN AND THE SUBSTANCE WAS FOUND AGAIN.  BOTH FORWARD FUEL CELLS WERE REMOVED FROM THE AIRCRAFT.  THE SPONGE-LIKE MATERIAL INSIDE THE WING ROOT HEADER TANK PORTION OF THE FUEL CELL WAS FOUND IN A DETERIORATED CONDITION AND CONTAMINATING THE ENTIRE FUEL SYSTEM.  NEW FUEL CELLS WERE ORDER.  (K)                                                                                                                                                                                             1L72 3O3  ORT3A16    E1CE                 
20060405002282006040500228EU  2006       4          5          2006FA0000266    120060217G21204783658519      FLEX DUCT                               ISRAEL1124  1124        4500102EU  GARRTTTFE731TFE731*     01518WP                              CABIN FLOOR DUCTDETERIORATED    C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW19290CA10907                  216                                     DURING C-CHECK, BY ACCESS OF FUSELAGE REPAIR, IT WAS FOUND THAT FLEXIBLE AIR CONDITIONING DUCTS WERE BADLY DETERIORATED.  FOAM ON INSIDE OF DUCTS WERE COMING LOOSE AND SOME OF DUCTS WERE COLLAPSED.  THESE DUCTS ARE JUST PLAIN OLD.  MFG TIME LIMITS DO NOT COVER THESE DUCTS AND DURING  800 HOUR C-CHECK AIRFRAME INSP THERE IS NOT A REQUIREMENT TO INSPECT INSIDE OF DUCTS FOR BLOCKAGE OR COLLAPSED DUCTS.  FLEX DUCTS CONNECT BELOW THE BLOW AND RUN UP SIDE OF THE FUSELAGE TO LWR AIR CONDITIONING VENTS.  THESE ARE NOT HOT AIR DUCTS, UNDER A UNFORSEEN CIRCUMSTANCE, POSES A POSSIBLE FIRE HAZARD IF DUCT TEMPERATURES GET HOT.  CALLED MFG TO GET FLEX DUCTS, PN CROSSED TO A NEW STYLE DUCT (PN BWT103080360A.)  (K)            2M72 4F4  F  A2SW    E6WE                 
20060405001752006040500175SO  2006       4          5          2006FA0000267    120060228G3260487862          SWITCH                                  PIPER PA31  PA31325     7103105SO  LYC   O540  TIO540*     41532EA                              RMLG            FAILED          B  DZZRO   OTHER                                                                                           P  NO WARNING INDICATION                                                         CRCRUISE         1                      GL0959815                       317612041                               AFTER SELECTING (GEAR DOWN), PILOT WAS UNABLE TO GET A GREEN LIGHT FOR RT MLG, IN EITHER NORMAL OR EMERGENCY EXTENSIONS.  GROUND OBSERVERS ADVISED RMLG WAS DOWN AND IB GEAR DOORS WERE OPEN.  UNEVENTFUL LANDING FOLLOWED.  INVESTIGATION REVEALED RMLG DOWNLOCK SWITCH FAILED ELECTRICALLY.   SWITCH WAS REPLACED, SEVERAL GEAR CYCLES ON JACKS.  AIRCRAFT TEST FLOWN, SATISFACTORY.  (K)                                                                                                                                                                                                                                                                                                                                                     1L72 3O3  O  A20SO   E14EA                
20060405001842006040500184NE  2006       4          5          2006FA0000268    220060302G72500292817220      RING                                    SNIAS 350   AS350B3     8680954EU  TMECA ARRIELARRIEL2B         NE                              ENGINE          CRACKED         B  HXSRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL05405AE                       3286        22103                       IN COMPLIANCE WITH AD AND SB, OUR MECHANIC WAS INSPECTING THE ABOVE DESCRIBED ENGINE AND FOUND THE COMPONENT LISTED BELOW TO BE OUT OF SERVICEABLE LIMITS AS INDICATED IN THE 2 DOCUMENTS.  REMOVED THE CONTAINMENT RING FROM SERVICE AND INSTALLED A NEW POST MOD TU-22 RING AS ADVISED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                  1G71 3U3  U  H9EU    E00054EN             
20060404002402006040400240NM  2006       4          4          2006FA0000269    120060215G2913123412          COVER           SMITHSIND               BOEING737   737*               NM                                                               SHUTOFF VALVE   CRACKED         D  IU6RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM01                6313                                                (REF NR:  204244/PH3) COVERED CRACKED.  PROBABLE CAUSE: FATIGUE.  REDESIGN COVER.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA16WE                        
20060405002352006040500235NM  2006       4          5          2006FA0000270    120060215G2913123412          COVER           SMITHSIND               BOEING737   737*               NM                                                               HYD SYS         CRACKED         D  IU6RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM01                6314                                                (REF NR: 204200/PH3)  COVER CRACKED, PROBABLE CAUSE, FATIGUE.  REDESIGN COVER.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F    RTA16WE                        
20060404002362006040400236NM  2006       4          4          2006FA0000271    120060213G2900271T00714       HOUSING         BOEING                  BOEING767   767*               NM                                                               HYDRAULIC SYS   CRACKED         B  IU6RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM01     28833      3087                                                (203230/FXS) HOUSING CRACK AT THE PRESSURE (INLET) PORT FOR THE CHECK VALVE BORE.  PROBABLE CAUSE: FATIGUE.  REDESIGN HOUSING.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F    RTA1NM                         
20060404002332006040400233NM  2006       4          4          2006FA0000272    120060213G3240511531          HOUSING         PNEUDRAULICS            BOEING737   737*               NM                                                               LANDING GEAR    CRACKED         B  IU6RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM01                                                                    (204174/PH3) HOUSING CRACKED IN THE BORE OF THE MOUNTING LUG.  PROBABLE CAUSE: FATIGUE.  REDESIGN HOUSING.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F    RTA16WE                        
20060327000022006032700002CE  2006       3          27         2006FA0000273    120060301G7120051313211       MOUNT                                   CESSNA175   175A        2072504CE                                                               ENGINE          CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE076997E1900                   56497                                   DURING VISUAL INSPECTION FOUND THE 0513132-11 UPPER LEFT HAND ENGINE MOUNT BRACKET IN THE 0513132-3 STRINGER ASSEMBLY CRACKED.  INSPECTION WAS PERFORMED DUE TO OTHER REPORTED FAILURES OF THIS BRACKET ON THE SAME MODEL OF AIRCRAFT.  RECOMMEND INSPECTION OF BRACKETS IN ALL AIRCRAFT WITH THE 0513132-3 ENGINE MOUNT STRINGER ASSEMBLY.                                                                                                                                                                                                                                                                                                                                                                                                     1H71 3O      3A17                         
20060327000342006032700034NM  2006       3          27         2006FA0000274    120060301G63205100400         HOSE                                    DOUG  MD900 MD900       3027375NM  PWC   PW207 PW207E           NE                              XMSN OIL        CRACKED         D      K   NONE                                                                                            KJ FLUID LOSS                WARNING INDICATION                                  ININSP/MAINT     1                      EA11902PD489  489               9000084                                 HOSE IS INSTALLED ON MD902 HELICOPTERS.  MD P/N IS 900D3409526-105.  HOSE IS USED FOR MAIN TRANSMISSION OIL COOLING.  FOUND LARGE ACCUMULATION OF OIL ON TRANSMISSION DECK AFTER FLIGHT.  HOSE WAS FOUND TO BE CRACKED IN ONE OF THE BELLOWS. (CORE OF HOSE IS STAINLESS STEEL BELLOWS WITH A COVERING OF STAINLESS STEEL BRAID).  REPLACED HOSE WITH NEW.                                                                                                                                                                                                                                                                                                                                                                                      1G72 3U3  UNCH19NM   E42NE                
20060327000452006032700045CE  2006       3          27         2006FA0000275    120060307G2420991059112       ALTERNATOR                              CESSNA206   206H        2073301CE  LYC   O540  IO540AC1A5       EA                              ENGINE          BURNED          C      HO  DEACTIVATE SYST/CIRCUITSOTHER                                                                   HJSELECT. POWER LOSS-50 PC   WARNING INDICATION        AFFECT SYSTEMS            CRCRUISE         1                      CE07     76   76                08255       L3083148E                   BATTERY TERMINAL LUG BURNT OFF DUE TO SHORT CAUSED BY TERMINAL ON WIRE HARNESS BREAKING OFF.  THIS CAUSED THE ALTERNATOR CONTROL UNIT TO FAIL (SMOKE) AND HEAVY ARCING AT TERMINAL LUG.  THERE WAS AN INDICATION OF NOT CHARGING ON G-1000 MFD AND PFD SCREENS.  THIS ALSO CAUSED FLUCUATION ON THE FUEL FLOW INDICATION.  SUSPECT SHORTED CABLE THRU ALTERNATOR ATTACHED TO ENGINE THRU ENGINE AND THEN THRU SENSOR.  NOTE: NO CIRCUIT BREAKER POPPED AND NO FUSEABLE LINK BETWEEN BATTERY HARNESS CONNECTED TO THE ALTERNATOR AND ALTERNATOR CONTROL UNIT.  SUSPECT WEAK TERMINAL AT ALTERNATOR ALONG WITH POOR INSTALLATION SUPPORT BY CLAMPS OR TIE-WRAPS.  CORRECTED AS REQUIRED WITH A MORE HEAVIER DUTY TERMINAL.                        1H71 3O3  ORTA4CE    1E4                  
20060327000462006032700046SO  2006       3          27         2006FA0000276    120060306G3230                SEQUENCE VALVE                          PIPER PA46  PA46350P    7104602SO                                                               NLG             DEFECTIVE       B      O   OTHER                                                                                           J  WARNING INDICATION                                                            APAPPROACH       1                      CE0355WH 1912                   4636204                                 LOUD NOISE REPORTED BY PILOT, AND FOUND NOSE GEAR DOOR ACUATOR ROD END BROKEN.  LANDING GEAR UNSAFE LIGHT STAYS ON WITH GEAR UP.  FOUND NOSE GEAR DOOR SEQUENCE VALVE INOPERTIVE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L71 3O    RTA25SO                        
20060327000472006032700047SW  2006       3          27         2006FA0000285    120060302G2730740101000       TORQUE TUBE                             MOONEYM20   M20J        5870219SW                                                               TRIM SYS        WORN            B  CTYRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL21913JN7274                   241184                                  EMPENNAGE TRIM CONTROL TORQUE FOUND TO HAVE A DEEP GROOVE FROM WEARING ON CAT TRACK/GROMMET WHERE IT PASSES THROUGH STIFFENERS.  THIS TUBE WAS ALSO WELD REPAIRED AT SOME TIME PREVIOUS THEN SWAPPED END FOR END SO TUBE WOULD WEAR ON A NEW SURFACE.  IT APPEARS THIS WAS DONE DURING AN AIRCRAFT REPAIR AFTER AN ACCIDENT.  NO DOCUMENTATION IN AIRCRAFT RECORDS OF THIS REPAIR.  NEW TUBE INSTALLED BY REPAIR STATION.  THIS AIRCRAFT HAD BEEN THROUGH NUMEROUS ANNUAL INSPECTIONS AND NOT REPLACED OR DOCUMENTED.                                                                                                                                                                                                                           1L71 3O      2A3                          
20060518002522006051800252GL  2006       5          18         2006FA0000286    120060227G7603                THROTTLE CABLE                          AMTR  SONEX SONEX       056085QGL                                                               COCKPIT         BINDING         G      A   UNSCHED LANDING                                                                                 R  PARTIAL RPM/PWR LOSS                                                          CRCRUISE         1                      GL03415KP20                     514                                     AIRCRAFT EXPERIENCED A LOSS OF POWER, AND A SUBSEQUENT FORCED LANDING RESULTING IN EXTENSIVE DAMAGE TO THE AIRCRAFT, DUE TO THE THROTTLE BEING STUCK IN THE IDLE POSITION. WHILE REDUCING POWER TO THE ENGINE PILOT EXPERIENCED BINDING IN THE THROTTLE CABLE , FURTHER ATTEMPTS TO FREE THE THROTTLE RESULTED IN THE THROTTLE BEING STUCK IN THE IDLE POSITION.  FOLLOW ON INSPECTIONS OF THE CARBURETOR AND ASSOCIATED LINKAGE FOUND EXCESSIVE PLAY IN THE CABLE BETWEEN THE THROTTLE CONTROL AND THE FIREWALL. THE EXCESS SLACK IN CABLE WAS NOT SECURED OR CLAMPED CAUSING THE CABLE ASSEMBLY TO BEND WHILE MOVING THE THROTTLE AND CAUSING BINDING.                                                                                        1L71 3O    NCEXPA1L71                     
20060330000032006033000003NE  2006       3          30         2006FA0000299    120060316G3020                HINGE                                   CONAERLA4   LA4200      5110310NE  LYC   O360  IO360A1A    41514EA                              CARB HEAT BOX   WORN            B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA232994P2470 59                956         L1997351A                   DURING ANNUAL INSPECTION FOUND ALTERNATE AIR VALVE HINGE WORN THRU.  REMOVED HEAT BOX ASSY AND FOUND BOX CRACKED 50 PERCENT AROUND MOUNTING FLANGE.  CRACK COULD NOT BE SEEN WITH BOX ON AIRCRAFT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O3  O  1A13    1E10                 
20060330000832006033000083NM  2006       3          30         2006FA0000300    120060315G2761BACS12HL4H10P   BOLT                                    BOEING737   7372H6      1384604NM                                                               SPOILER         BROKEN          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO25902WG                       22620                                   DURING A CHECK FOUND LOWER AFT BOLT HEAD BROKEN AT ACTUATOR TO MANIFOLD MOUNT FLANGE.  NO OTHER DAMAGE FOUND AND NO LEAK SEEN.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F    RTA16WE                        
20060331000702006033100070CE  2006       3          31         2006FA0000301    120060304G55510431148         ATTACH FITTING                          CESSNA150   152         2071835CE                                                               HORIZONTAL STAB CRACKED         B      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP214896813660                  15281080                                PART ATTACHES VERTICAL STABILIZER SPAR TO HORIZONTAL STABILIZER SPAR ATTACH FITTING P/N 0432004-9.  PROBABLE CAUSE IS HIGH ACTT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1H71 3O    NT3A19                         
20060411000522006041100052SO  2006       4          11         2006FA0000302    220060310G74146310            MAGNETO                                 CESSNA185   185F        2072820CE  CONT  O550  IO550D      17042SO                              ENGINE          CHAFED          C      O   OTHER                                                                                           E  VIBRATION/BUFFET                                                              CRCRUISE         1                      WP23     126                                680081                      ROUGH MAG IN FLIGHT.  FOUND THAT CAPACITOR LEAD WAS INSTALLED ON POINTS BACKWARDS ALLOWING LEAD TO CONTACT MAIN DRIVE GEAR.  GEAR HAD EATEN THROUGH INSULATION AND ALL BUT 2 STRANDS OF THE WIRE.  MAG WAS NEARING COMPLETE FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H71 3O3  O  3A24    E3SO                 
20060411000552006041100055SO  2006       4          11         2006FA0000303    220060310G74146310            MAGNETO                                 CESSNA185   185F        2072820CE  CONT  O550  IO550D      17042SO                              ENGINE          CHAFED          C      O   OTHER                                                                                           E  VIBRATION/BUFFET                                                              CRCRUISE         1                      WP23PKMCD126                                680081                      ROUGH MAG IN FLIGHT.  FOUND THAT CAPACITOR LEAD WAS INSTALLED ON POINTS BACKWARDS ALLOWING LEAD TO CONTACT MAIN DRIVE GEAR.  GEAR HAD EATEN THROUGH INSULATION AND ALL BUT 2 STRANDS OF THE WIRE.  MAG WAS NEARING COMPLETE FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H71 3O3  O  3A24    E3SO                 
20060411000532006041100053SO  2006       4          11         2006FA0000304    220060310G74146310            MAGNETO                                 CESSNA185   185F        2072820CE  CONT  O550  IO550D      17042SO                              ENGINE          CHAFED          C      A   UNSCHED LANDING                                                                                 E  VIBRATION/BUFFET                                                              CRCRUISE         1                      WP23PKMCD126                                680081                      ROUGH MAG IN FLIGHT.  FOUND THAT CAPACITOR LEAD WAS INSTALLED ON POINTS BACKWARDS ALLOWING LEAD TO CONTACT MAIN DRIVE GEAR.  GEAR HAD EATEN THROUGH INSULATION AND ALL BUT 2 STRANDS OF THE WIRE.  MAG WAS NEARING COMPLETE FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H71 3O3  O  3A24    E3SO                 
20060411000542006041100054SO  2006       4          11         2006FA0000305    220060310G74146310            MAGNETO                                 CESSNA185   185F        2072820CE  CONT  O550  IO550D      17042SO                              ENGINE          CHAFED          C      O   OTHER                                                                                           E  VIBRATION/BUFFET                                                              CRCRUISE         1                      WP23PKMCD126                                680081                      ROUGH MAG IN FLIGHT.  FOUND THAT CAPACITOR LEAD WAS INSTALLED ON POINTS BACKWARDS ALLOWING LEAD TO CONTACT MAIN DRIVE GEAR.  GEAR HAD EATEN THROUGH INSULATION AND ALL BUT 2 STRANDS OF THE WIRE.  MAG WAS NEARING COMPLETE FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H71 3O3  O  3A24    E3SO                 
20060411001062006041100106SO  2006       4          11         2006FA0000307    220060208G8500                ENGINE          CONT                    BEECH 58    58          1152740CE  CONT  O550  IO550C           SO  HARTZLHCJ3Y PHCJ3YF1    GL  RT WING         UNKNOWN         H      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW11106GA           824277R     TH437       824277R     ED3372          RT ENGINE WAS STARTED AND PILOT NOTICED LOW OIL PRESSURE.  INSTALLED ANOTHER GAUGE IN LINE TO VERIFY PROBLEM RAN ENGINE, OIL PRESSURE CERTIFIED LOW.  CHANGED OIL AND INSPECTED FILTER.  FOUND NO OBVIOUS PROBLEMS, STARTED ENGINE, HAD NO OIL PRESSURE, PULLED RELIEF VALVE.  DETERMINED THAT SOMETHING INSIDE THE ENGINE WAS COMING APART.  REMOVED ENGINE TO SEND BACK TO ENGINE OVERHAULER.  (K)                                                                                                                                                                                                                                                                                                                                            1L72 3O3  O  3A16    E3SO    5  CP36EA    
20060411000342006041100034EA  2006       4          11         2006FA0000309    220060224G732063B23440        FLOW DIVIDER                            CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA  MCAULY1A170 1A170E      GL  ENGINE          CORRODED        B      O   OTHER                                                                                           R  PARTIAL RPM/PWR LOSS                                                          TXTAXI/GRND HDL  1                      CE07696MS91   50                172S10079   L3242151E   JHA7660         AIRCRAFT FAILED TO START & RUN. NO FUEL FLOW INDICATED ON G-1000. TROUBLSHOOT FUEL SYS & FOUND FUEL NOT PASSING THROUGH FLOW DIVIDER. SENT UNIT FOR REPAIR. AT THAT TIME AIRCRAFT HAD 41.0 HRS SINCE NEW. SECOND TIME AT 91.0 HRS.SINCE NEW, HAD THE SAME PROBLEM AS INDICATED AS ABOVE.  BOTH TIMES FOUND THE VALVE STEM STUCK INSIDE THE BORE. APPEARS TO BE A RUST/BROWN COLORED CONTAMINATION AND SLIGHT SCORING. FLOWED FUEL INTO TEST JAR AND NO PARTICLES WAS NOTED ON AIRCRAFT FUEL SYSTEM. APPEARS TO BE CORROSION INSIDE BORE. B&S AIRCRAFT POLISHED VALVE STEM AND BORE, OPS. CK. OK.                                                                                                                                                1H71 3O3  ONT3A12    1E10    5  NP857     
20060411000362006041100036CE  2006       4          11         2006FA0000311    120060224G2842                FLOAT                                   CESSNA172   172H        2072424CE                                                               FUEL INDICATION FAILED          D      K   NONE                                                                                            N  FALSE WARNING                                                                 ININSP/MAINT     1                      NM013786R                       17255586                                LEFT WING FUEL GAGE REGISTERED EMPTY. UPON INSPECTION OF THE FLOAT ASSEMBLY, FOUND FLOAT TO BE ONE THIRD FULL OF FUEL. METAL FLOAT HAS MULTIPLE PIN HOLES. RIGHT SIDE WAS FINE - NO LEAKS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1H71 3O    NT3A12                         
20060411000372006041100037EA  2006       4          11         2006FA0000312    220060224G7261156F00512D0260  HOSE                                    PIPER PA31T PA31T       7103124SO  PWA   PT6   PT6A28           EA  HARTZLHCB3T HCB3TN3     GL  ENGINE OIL      DAMAGED         B      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      GL11220FS                       31T7620052  PCE51064    BU13482         DURING CLIMB, PILOT NOTED RT OIL PRESS FLUTUATING SLIGHTLY & SLOWLY FALLING.  ENGINE SHUTDOWN & RETURNED TO BASE.  INVESTIGATION REVEALED A LEAKING OIL COOLER HOSE. LEAK POINT COVERED BY FIRESLEEVING.  HOSE REMOVED & SLEEVING CUT OPEN REVEALING WIRE BRAID.  EXTERNAL EXAMINATION DID NOT INDICATE ANY OBVIOUS VISIBLE DEFECT.  FURTHER INVESTIGATION USING A FLEXIBLE LIGHT SOURCE REVEALED A FAILED INNER WALL MID-WAY IN THE HOSE AND ON THE INSIDE RADIUS OF THE HOSE BEND. THE HOSE MANF. DATE 01/04.  PROBABLE CAUSE WAS INCORRECT HANDLING OR INSTALLATION OF HOSE AT SOME POINT WHICH RESULTED IN KINKING OF THE HOSE AND EVENTUAL FAILURE OF THE INNER WALL.                                                                      1L72 3T4  T  A8EA    E4EA    6  CP15EA    
20060411000382006041100038CE  2006       4          11         2006FA0000313    120060226G5346051313211       BRACKET                                 CESSNA175   175         2072502CE                                                               ENGINE MOUNT    CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE077536M2641                   55836                                   DURING VISUAL INSPECTION OF UPPER ENGINE MOUNT BRACKETS IN THE UPPER ENGINE MOUNT STRINGER ASSEMBLIES, FOUND THE L/H 0513132-11 BRACKET CRACKED. INSPECTION WAS PERFORMED DUE TO RECENT REPORTS OF FINDING BRACKETS CRACKED ON LIKE MODELS OF AIRCRAFT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1H71 3O    NT3A17                         
20060411000402006041100040CE  2006       4          11         2006FA0000318    120060227G5346051313211       BRACKET                                 CESSNA175   175         2072502CE                                                               ENGINE MOUNT    CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE07141JA4791                   55224                                   FOUND THE LEFT UPPER ENGINE MOUNT BRACKET P/N 0513132-11 CRACKED THROUGH AROUND THE WASHER. BRACKET IS LOCATED AT THE FRONT OF THE 0513132-3 ENGINE MOUNT STRINGER AND IS DIFFICULT TO SEE DURING ROUTINE INSPECTIONS. INSPECTION WAS PERFORMED DUE TO SEVERAL OTHER CASES OF THE BRACKET BEING FOUND CRACKED ON LIKE AIRCRAFT.                                                                                                                                                                                                                                                                                                                                                                                                                 1H71 3O    NT3A17                         
20060411000422006041100042CE  2006       4          11         2006FA0000320    120060301G5346051313211       BRACKET                                 CESSNA175   175A        2072504CE                                                               ENG MOUNT       CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE076997E1900                   56497                                   DURING VISUAL INSPECTION FOUND THE 0513132-11 UPPER RIGHT HAND ENGINE MOUNT BRACKET IN THE 0513132-4 STRINGER ASSEMBLY CRACKED. INSPECTION WAS PERFORMED DUE TO OTHER REPORTED FAILURES OF THIS BRACKET ON THE SAME MODEL OF AIRCRAFT. RECOMMEND INSPECTION OF BRACKETS IN ALL AIRCRAFT WITH THE 0513132-4 ENGINE MOUNT STINGER ASSEMBLY.                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3O      3A17                         
20060411000432006041100043CE  2006       4          11         2006FA0000321    120060301G554105310051        RIB                                     CESSNA172   172         2072402CE                                                               RUDDER          MISSING         D      K   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      NM096775A2262                   28875                                   RUDDER WAS REMOVED TO REPLACE CRACKED CORRUGATED SKIN BETWEEN LOWER TWO RIBS. ON SKIN REMOVAL, IT WAS DISCOVERED THAT SLANT RIB 0531005-1, (EXTENSION OF REAR SPAR) WAS MISSING. THERE WERE NO HOLES DRILLED IN BOTTOM RIB P/N 0531001-25 OR RIB P/N 0531001-22 TO WHICH THE SLANT RIB ATTACHES. LOGBOOK INDICATES THAT RUDDER WAS NEVER REPLACED OR REPAIRED, SO THE ASSUMPTION IS THAT THE PART WAS LEFT OUT DURING AIRCRAFT CONSTRUCTION. NEW RIB WAS INSTALLED.                                                                                                                                                                                                                                                                             1H71 3O    NT3A12                         
20060413002592006041300259    2006       4          13         2006FA0000325    120060314G251071513           SEAT FRAME                                                                                                                                              BROKEN          B      K   NONE                                                                                            O  OTHER                                                                         TXTAXI/GRND HDL  1                      SW15116SG544  50                                                        THE LOWER SEAT FRAME CONSISTS OF A PERIMETER RECTANGULAR TUBE FRAME THAT HAS THE ENDS OF STEEL STRAPS WELDED TO IT TO FORM A LOOSE WEBBING ASSEMBLY WHICH SUPPORTS THE SEAT CUSHION. DURING A PREFLIGHT THE PILOT NOTICED THE SEAT SAGGING AND FOUND THE ENDS OF TWO STRAPS HAD BROKEN WELDS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             
20060413002712006041300271    2006       4          13         2006FA0000326    420060407G3421                ART HORIZION                            RAYTHNDH125 HAWKER800XP 7150012CE                                                               COCKPIT         MISWIRED        D      K   NONE                                                                                            O  OTHER                                                                         TXTAXI/GRND HDL  1                      NE01875LP                       258308                                  PILOT REPORTED STANDBY ARTIFICIAL HORIZON ILS NEEDLES MOVE IN OPPISITE DIRECTION OF #1 AND #2 ILS NEEDLES ON ILS APPROACH.  CONFIRMED REPORT.  FOUND THAT ARKANSAS AEROSPACE COMPLETION DRAWINGS( WERE NOT CORRECT WHEN COMPARED TO HONEYWELL RNZ-850 INSTALLATION MANUAL.  RNZ-850 PIN B78 VOR LFT DEVIATION WAS WIRED TO STANDBY HORIZON (JET ADI-322B) PIN G NAV DEVIATION +RT.  RNZ-850 PIN B75 DEV RTN WAS WIRED TO ADI-322B PIN H NAV DEVIATION + LT.  SWAPPED WIRES AT ADI-322B AND TESTED.  ILS DEVIATION LEFT AND RIGHT NOW MATCHES PRIMARY ILS DISPLAYS.                                                                                                                                                                              2L72 4F    RTA3EU                         
20060412000402006041200040SO  2006       4          12         2006FA0000327    220060313G7414                IMPULSE COUPLING                        BEECH 95    95B55       1152729CE  CONT  O470  IO470L      17026SO                              MAGNETO         RUSTED          B  YEBRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE052278S448                    TC2110                                  DURING A ROUTINE INSP, ALL MAGNETOS WERE REMOVED FOR POINTS AND CONDENSER REPLACEMENT.  RUST WAS FOUND ON THE FLYWEIGHT/AXLE AREA OF THE IMPULSE COUPLING.  A WEAR CHECK WAS MADE AND IT WAS DETERMINED THAT ALL COUPLINGS FAILED IAW MSB.  NOTE:  THE FLYWEIGHT/ AXLE PIN WEAR IS IN EXCESS OF .014 AND MAY BE DUE TO RUST.  THIS AREA OF INSPECTION MAY BE OVERLOOKED DUE TO THE OMISSION OF MANY IMPULSE COUPLINGS INSTALLED ON ENGINE NOT INCLUDED IN AD.  (K)                                                                                                                                                                                                                                                                              1L72 3O3  ORT3A16    3E1                  
20060412000782006041200078EA  2006       4          12         2006FA0000328    220060309G7414M3548           SHAFT                                   PIPER PA28  PA28R201    7102816SO  LYC   O360  IO360C1C6   41514EA  MCAULY2D34C B2D34C213   GL  MAGNETO         SHEARED         B  UC2RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL195321U           98070601    2844042     L2958751A   002421          ENGINE RUNUP INDICATED A DEAD MAGNETO.  REMOVED AND DISASSEMBLED MAGNETO HOUSING.  FOUND ROTOR SHAFT SHEARED OFF AT BOTTOM OF CAM SLOT.  A FEW CRACKED SHAFTS HAVE BEEN FOUND AT 500 HR INSPECTIONS.  RECOMMEND CLOSE INSPECTION OF THIS AREA AT REPAIR AND OVERHAUL.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L71 3O3  O  2A13    1E10    5  CP7EA     
20060413001682006041300168GL  2006       4          13         2006FA0000330    220060410G723059084           STATOR                                                                     WILINTFJ44  FJ44        66000GL                              COMPRESSOR      DETERIORATED    B  WI5RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL23                                        126173                      3RD STAGE IP STATOR ABRADABLE WAS EXFOLIATING CAUSING THE 3RD STAGE IP BLADES TO CONTACT THE STATOR ABRADABLE.  THIS RESULT IN N1 LOCK-UP.  BASED UPON HARDWARE EVALUATION, ROOT CAUSE OF THE ABRADABLE EXFOLIATING WAS DUE TO THE WATER WASH PROCEDURES (COASTAL A/C) NOT BEING FOLLOWED PG THE ENGINE MM.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                       4  F          E3GL                 
20060412000382006041200038SO  2006       4          12         2006FA0000331    120060306G2140A23D0475        REGULATOR                               PIPER PA23  PA23250     7102308SO  LYC   O540  TIO540*     41532EA                              CABIN HEATER    LEAKING         B  GFVRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM136549A                       277954006                               AIRCRAFT RECEIVED FROM NEW OWNER WANTING HEATER MADE OPERATIONAL: TOTALLY DEACTIVATED.  REPLACED HEATER ASSY DUE TO EXTREME DETORATION.  FUEL REGULATOR REPLACED DUE TO LEAKAGE AND FAILURE TO REGULATE FOUND INLET PORT PARTIALLY PLUGGED BY CORROSION BY-PRODUCTS AND REMNANTS OF DAMAGED THREADS.  N/E REPAIRABLE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                      1L72 3O3  O  1A10    E14EA                
20060413002722006041300272CE  2006       4          13         2006FA0000332    120060327G5412569500511       BULKHEAD                                CESSNA340   340A        2076405CE                                                               LT WING         CORRODED        D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL25340JY3462                   340A0979                                DURING 500 HR. VISUAL INSPECTION PER AD2000-01-16 PARA (D) FOUND LEFT ENGINE AFT CANTED BULKHEAD #5695005-11 AND SUPPORT DOUBLER #5695005-6 CORRODED AND HEAT DAMAGED COMPLETELY THROUGH STRUCTURE.  DAMAGE LOCATED NEAR OUTBOARD SECTION ABOVE EXHAUST ELBOW CUT OUT AREA.                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L72 3O      3A25                         
20060510002492006051000249CE  2006       5          10         2006FA0000333    120060327G5412569500511       BULKHEAD                                CESSNA340   340A        2076405CE                                                               LT WING         CORRODED        D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL25340JY3462                   340A0979                                DURING 500 HR. VISUAL INSPECTION PER AD2000-01-16 PARA (D) FOUND LEFT ENGINE AFT CANTED BULKHEAD NR 5695005-11 AND SUPPORT DOUBLER NR 5695005-6 CORRODED AND HEAT DAMAGED COMPLETELY THROUGH STRUCTURE.  DAMAGE LOCATED NEAR OB SECTION ABOVE EXHAUST ELBOW CUT OUT AREA.                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 3O      3A25                         
20060511002502006051100250EA  2006       5          11         2006FA0000335    220060322G72103013132         SLEEVE          PWA         PT6A27                                         PWA   PT6   PT6A27      52043EA                              ENGINE          SHIFTED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO03          805   42083100                PCE42083                    OPERATOR ATTEMPTED TO ROTATE THE PROPELLER DURING A PREFLIGHT CHECK AND NOTED PROP SHAFT LOOSENESS AND DRAG. THE ENGINE WAS REMOVED FOR REPAIR. EXAMINATION OF THE 2ND STAGE CARRIER IN THE RGB REVEALED THAT THE SLEEVE USED TO REPAIR THE NR 5 BEARING JOURNAL HAD SHIFTED OFF OF THE JOURNAL. THERE WAS NO COLLATERAL DAMAGE DUE TO SLEEVE SHIFT.                                                                                                                                                                                                                                                                                                                                                                                                   4  T          E4EA                 
20060414000942006041400094SO  2006       4          14         2006FA0000337    120060406G2434ALU8539LS       ALTERNATOR                              PIPER PA46  PA46350P    7104602SO                                                               ENGINE          BURNED          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM09110ST142                    4636373                                 OUTPUT POST WAS LOOSE AND BURNED.  TERMINAL ON OUTPUT WIRE GOING TO BOSS BAR WAS BURNED, MELTED, AND SEPARATED FROM ALTERNATOR.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L71 3O    RTA25SO                        
20060417000452006041700045SO  2006       4          17         2006FA0000338    120060317G5711PA28140         SPAR                                    PIPER PA28  PA28140     7102802SO  LYC   O320  O320*       41508EA                              WING            CORRODED        D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE036399W                       2820467                                 DURING 100 HR INSPECTION ON REAR SPAR CHANNEL, RIVET HEADS WERE POPPED ON BOTH SIDES.  A COMPLETE INSPECTION REVEALED SEVERE CORROSION BETWEEN CHANNEL AND STEEL PLATES.  ALSO, SEVERE CORROSION EXISTED BETWEEN REAR IB ATTACH FITTINGS TO SPAR.  THE ATTACH FITTINGS HID VIEW FROM THE OUTSIDE.  WITH NO INSPECTION PANELS IN THAT AREA THE INSPECTION HAS TO BE MADE THROUGH THE IB RIB LOOKING AFT.  THE STRUCTURAL INTEGRITY OF THE LT SPAR ATTACH AREA WAS SEVERELY COMPROMISED.  (K)                                                                                                                                                                                                                                                     1L71 3O3  O  2A13    E274                 
20060414000922006041400092SO  2006       4          14         2006FA0000339    120060317G571162054000        SPAR                                    PIPER PA28  PA28140     7102802SO                                                               LT WING         CORRODED        C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE036399W3744                   2820467                                 DURING 100 HR INSPECTION ON REAR SPAR CHANNEL, RIVET HEADS WERE POPPED ON BOTH SIDES.  A COMPLETE INSPECTION REVEALED SEVERE CORROSION BETWEEN CHANNEL AND STEEL PLATES.  ALSO, SEVERE CORROSION EXISTED BETWEEN REAR IB ATTACH FITTINGS TO SPAR.  THE ATTACH FITTINGS HID VIEW FROM THE OUTSIDE.  WITH NO INSPECTION PANELS IN THAT AREA THE INSPECTION HAS TO BE MADE THROUGH THE IB RIB LOOKING AFT.  THE STRUCTURAL INTEGRITY OF THE LT SPAR ATTACH AREA WAS SEVERELY COMPROMISED.  (K)                                                                                                                                                                                                                                                     1L71 3O      2A13                         
20060419002072006041900207CE  2006       4          19         2006FA0000340    120060210G3397L143J20         WIRE                                    BEECH 36    A36         1151604CE  CONT  O550  IO550B           SO  MCAULY3A32C D3A32C*     GL  RT WING NAV LITECHAFED          B      O   OTHER                                                                                           J  WARNING INDICATION                                                            CRCRUISE         1                      WP23806NH                       E2702       686012      912713          PILOT REPORTED NAVIGATION LIGHT BREAKER SWITCH (POPPED) IN FLIGHT AND WAS NOT ABLE TO RESET.  MAINTENANCE PERSONAL TROUBLESHOT NAVIGATION LIGHT SYSTEM AND FOUND A SHORT IN THE WIRING IN THE RT WING AT APPROXIMATE WING STATION 162.5.  A NEW WIRE WAS PULLED THROUGH TO REPLACE THE OLD WIRE.  TIME IN SERVICE IS A FACTOR IN THIS OCCURRENCE.  ALSO IN SERVICE IS A FACTOR IN THIS OCCURRENCE.  ALSO THE WIRE LAYS IN A STRINGER CHANNEL AND HAS NO OTHER MEANS OF SUPPORT OTHER THAN GLUED IN STRIPS AT VARIOUS INTERVALS TO KEEP THE WIRE IN THE CHANNEL.  THERE IS NO ACCESS TO THIS WIRE FROM WING STA 122.75 TO 191.00.  THERE SHOULD BE A PLASTIC CONDUIT TUBING FOR THIS WIRE TO RUN THROUGH.  (K)                                   1L71 3O3  O  3A15    E3SO    5  CP21EA    
20060419002192006041900219NM  2006       4          19         2006FA0000342    120060315G3520417N31002933E   CABLE                                   BOEING737   7373G7      1384595NM  GE    CFM56 CFM563B1    13802NE                              PX OXY SYS      MISROUTED       B  LH6YK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA35370WL                       24011                                   (REF: ATC0662) THE ACTUATING CABLE TO THE CHEMICAL OXYGEN GENERATORS ON PASSENGER SERVICE UNITS WERE FOUND INCORRECTLY ROUTED.  IE: IT WAS UNDER THE PIN AND RESTING ON THE PLASTIC MOULDING.  DEFECT RAISED AS AN (IORS) INTERNAL OCCURRENCIES REPORT AND UPGRADED TO MALFUNCTION AND DEFECT REPORT DUE TO SYSTEM BEING (EMERGENCY).  (K)                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F4  FRTA16WE   E2GL                 
20060419002062006041900206SO  2006       4          19         2006FA0000343    220060401G7414M3081           POINTS                                  AMTR  LANCARLC41550FG   5150001GL  CONT  O550  TSIO550C         SO                              RT MAGNETO      BROKEN          D      O   OTHER                                                                                           L  NO TEST                                                                       TXTAXI/GRND HDL  1                      NM0979HR                        41017       802655                      ON ENGINE GROUND RUN PRIOR TO FLIGHT MAGNETO CHECK FOUND RT MAGNETO HAD FAILED INSPECTION FOUND POINTS BROKEN PICTURE INCLOSED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L71 3O3  ORTEXPA1L71E5SO                 
20060419003212006041900321SO  2006       4          19         2006FA0000344    120060317G27318646002         CABLE                                   PIPER PA44  PA44180     7104402SO  LYC   O360  O360*       41514EA                              FUSELAGE        JAMMED          B  RJURK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP19259AT3151                   4496080                                 PILOT REPORTED THAT STABILATOR TRIM WAS JAMMING IN THE NOSE-UP POSITION.  IT WAS DISCOVERED THAT TRIM CABLE TURNBUCKLE WAS CATCHING ON BULKHEAD JAMMING CABLE.  CABLE TENSIONS WERE ADJUSTED TO SPECIFICATIONS AND PROBLEM REPEATED.  RECOMMEND SLIGHT RADIUS OF MATERIAL AND REINFORCEMENT OF AFFECTED AREA TO PREVENT RECURRENCE OF PROBLEM.  (K)                                                                                                                                                                                                                                                                                                                                                                                             1L72 3O3  O  A19S0   E286                 
20060419003122006041900312CE  2006       4          19         2006FA0000345    120060215G3230NAS4645A15      BOLT                                    CESSNA177   177RG       2073709CE                                                               NLG             BACKED OUT      D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE0352643                       177RG1225                               NOSE LANDING GEAR FAILED TO LOCKDOWN.  THE NAS404-5A15 BOLT THAT BOTH SECURES AND PROVIDES A PIVOT POINT FOR THE LOCK ASSY TO THE DRAG LINK HAD BACKED OUT OF THE DRAG LINK TOTALLY DISCONNECTING THE LOCK ASSY FROM THE DRAG LINK.  THERE WAS EVIDENCE OF RED LOCKTITE IN THE DRAG LINK AS IS REQUIRED BY THE SRM BUT IT BACKED OUT ANY WAY.  THIS BOLT IS NOT A DRILLED HEAD BOLT, BUT I RECOMMEND THAT IT BE REPLACED WITH ONE TO AVOID REOCCURRENCE.  (K)                                                                                                                                                                                                                                                                                   1H71 3O      A20CE                        
20060419003272006041900327CE  2006       4          19         2006FA0000346    120060320G37101U478003        PUMP                                    BEECH 33    F33A        1151425CE  CONT  O520  IO520BB     17032SO                              ENGINE          WORN            B  VJ3RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP075521A304                    CE1338      830070R                     PILOT REPORTED THAT AT 1700 RPM INSTRUMENT AIR PRESSURE (3.5 HG) UPON TROUBLESHOOTING OF THE INSTRUMENT AIR PRESSURE SYSTEM TECHNICIAN FOUND AIR PUMP WAS NOT PRODUCING ENOUGH PRESSURE.  PROBABLE CAUSE IS UNKNOWN AT THIS TIME.  NO RECOMMENDATION AT THIS TIME EITHER.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L71 3O3  O  3A15    E5CE                 
20060419003202006041900320EA  2006       4          19         2006FA0000347    220060324G7322105267          CARBURETOR                              CESSNA150   152         2071835CE  LYC   O235  O235L2C     41505EA                              ENGINE          CONTAMINATED    H  CE8SK   NONE                                                                                            Y  ENGINE STOPPAGE                                                               TOTAKEOFF        1                      SO1525566                       15280734    RL2324815                   CONTAMINANT FOUND INSIDE OF THE MAIN JET OF THE CARBURETOR.  ENGINE QUIT ON TAKE OFF ROLL.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1H71 3O3  ONT3A19    E223                 
20060502000042006050200004    2006       5          2          2006FA0000348    120060227G8011MHB4016R        STARTER                                                                                                                                 ENGINE          NOISY           B  WS9RO   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      NM07                                                                    STARTER WHINING, AND WILL NOT START ENGINE.  WILL START WITH HAND PROP, BUT WHINES.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  
20060419003242006041900324NM  2006       4          19         2006FA0000349    120060328G5711                SPAR CAP                                UNIVAR415   415C        0420302NM  CONT  C90   C90*        17009SO                              RT WING         CRACKED         B  N5DRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP153158H                       3783                                    DURING ACCOMPLISHMENT OF SB NR 32, A 0.625 INCH LONG, SPANWISE CRACK WAS NOTED ON THE RT UPPER SPAR CAP IN THE MAIN SPAR CENTER SECTION APPROX 0.250 INCH IB OF THE CENTER SECTION OB END.  PROBABLE CAUSE IS UNKNOWN.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L71 3O3  O  A718    E252                 
20060419003222006041900322NM  2006       4          19         2006FA0000350    120060321G274007322P11070     BALL END                                BOEING737   737*               NM                                                               HORIZ STABILIZERFOD             B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM01                0728                                                THE MAJOR COMPONENTS ARE BEYOND ECONOMICAL REPAIR (SCRAP).  THE DAMAGE WAS CAUSED BY A FOREIGH OBJECT, PROBABLY LOOSE BALL.  THIS CAN HAPPEN ANYTIME THE BALLNUT ASSY IS REMOVED FROM THE SCREWSHAFT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F    RTA16WE                        
20060502000062006050200006    2006       5          2          2006FA0000351    120060320G8011ES6462751       STARTER                                                                                                                                 ENGINE          TIGHT           B  WS9RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM07                                                                    STARTER IS TOO TIGHT AND WOULD NOT TURN.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             
20060419003282006041900328CE  2006       4          19         2006FA0000352    120060322G5312071220510       BULKHEAD                                CESSNA182   182A        2072704CE  CONT  O470  O470L       17026SO                              AFT FUSELAGE    CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM072233G                       51533       668916L                     BULKHEAD, PN 071220510, CRACKED AT TIE DOWN HOLE.  BULKHEAD, PN 0712206 CRACKED AT BOLT HOLES ATTACHMENT TO ELEVATOR BELLCRANK SUPPORT MOUNT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O3  ONT3A13    E273                 
20060419003232006041900323CE  2006       4          19         2006FA0000353    120060322G5312071220510       BULKHEAD                                CESSNA182   182A        2072704CE  CONT  O470  O470L       17026SO                              FUSELAGE TAIL   CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM072233G                       51533       668916L                     BULKHEAD, PN 071220510, CRACKED AT TIE DOWN HOLE.  BULKHEAD, PN 0712206, CRACKED AT BOLTHOLES ATTACHMENT TO ELEVATOR BELLCRANK SUPPORT MOUNT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O3  ONT3A13    E273                 
20060502000052006050200005    2006       5          2          2006FA0000354    120060228G81004066109005      TURBOCHARGER                                                                                                                            ENGINE          WEAK            B  WS9RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM07     2                                                              TURBO CHARGER WOULD NOT MAKE ENOUGH BOOST.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           
20060419003252006041900325NE  2006       4          19         2006FA0000355    220060318G73200292858570      HMU                                     UROCOPEC130 EC130B4     8680989EU  TMECA ARRIELARRIEL2B         NE                              ENGINE          UNKNOWN         C      A   UNSCHED LANDING                                                                                 EJ VIBRATION/BUFFET          WARNING INDICATION                                  LDLANDING        1                      WP1311QF                        3482                                    PRECAUTIONARY LANDING DUE TO BANG HEARD IN FLIGHT BY PILOT.  NORMAL LANDING ACCOMPLISHED W/O ACCIDENT, OR INJURIES.  AC LANDED ON PRIVATE PROPERTY.  UPON LANDING, GOVERNOR WARNING LIGHT ILLUMINATED.  SUBSEQUENT INVESTIGATIVE TROUBLESHOOTING REVEALED VEMD TO DISPLAY A CODE (192) HMU FAULT, INDICATING A FAILURE OF EBCAU STEPPER MOTOR.  VISUALLY INSPECTED ENG ASSY AND SURGE BLEED VALVE ASSY.  NO DEFECTS NOTED, HMU AND EBCAU UNITS WERE REPLACED WITH SERVICABLE UNITS.  GROUND AND FLIGHT TESTS PROVED GOOD WITH NO INDICATED ERROR CODES.  AC TEST FLOWN BACK TO MAINTENANCE BASE WITH NO FURTHER PROBLEMS NOTED.  DETERMINED THE INITIAL BANG HEAR IN FLIGHT WAS MOST LIKELY A COMPRESSOR STALL DUE TO THE MALFUNCTION HMU.  (K) 1G72 3U3  U  H9EU    E00054EN             
20060419003262006041900326CE  2006       4          19         2006FA0000356    120060313G710010191000495     DUCT                                    BEECH 200   B200        1152922CE                                                               LT ENGINE       CRACKED         B  EHHRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA17326PG                       BB1709                                  LT ENGINE LOWER AFT COWLING, LWR DUCT FOUND CRACKED ABOUT 80 PERCENT ITS ENTIRE WIDTH ALONG FIRST RIVET ROW.  REMOVED CRACKED DUCT AND FOUND NOT TO BE ROLLED ENOUGH.  THIS PUT STRESS ON RIVET ROW.  NEW SPARE PART ORDER FROM MFG WAS ROLLED CORRECTLY AND FIT WITHOUT STRESS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L72 4T      A24CE                        
20060418002182006041800218EA  2006       4          18         2006FA0000357    220060313G73202576543         SERVO                                   CESSNA206   206H        2073301CE  LYC   O540  IO540AC1A5       EA                              ENGINE FUEL SYS INOPERATIVE     B  EHHRK   NONE                                                                                            Y  ENGINE STOPPAGE                                                               TXTAXI/GRND HDL  1                      EA17236KS                       20608236                                AIRCRAFT LANDED AND ENGINE QUIT.  TO RESTART ENGINE MIXTURE HAD TO PULL MIXTURE BACK TO .5 INCH OF IDLE CUT TO KEEP ENGINE RUNNING.  TRIED TO ADJUST IDLE MIXTURE WITHOUT SUCCESS.  AT THE ADJUSTMENT LEANEST SETTING THERE WAS STILL A 600 RPM RAISE WHEN MIXTURE PULLED TO IDLE CUT OFF.  REMOVED SERVO AND SENT.  REINSTALLED ON RETURN WITH SMALL ADJUSTMENTS ENGINE RAN SATISFACTORY.  THIS SAME SYMPTOMS SHOW ON ANOTHER AC WITH SAME PN SERVO.  THE AIRCRAFT HAD 129 HOURS, THIS SERVO EXCHANGED FOR AN OVERHAULED UNIT.  TECH SUPPORT STATED THAT THE DIAPHRAGMS HAVE SHIFTED AND THE METERING SEATS NEEDED POLISHING.  (K)                                                                                                             1H71 3O3  ORTA4CE    1E4                  
20060419002032006041900203NM  2006       4          19         2006FA0000358    120060321G274007322P11070     BALL SCREW                              BOEING737   737*               NM                                                               STABILIZER      FOD             B  N9GRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM01                0728                                                FOREIGH OBJECT DAMAGE DISCOVERED DURING INSPECTION OF BALLSCREW ASSY BY SUBCONTRACTOR.   THE MAJOR COMPONENTS ARE BEYOND ECONOMIC REPAIR (SCRAP).  THE DAMAGE WAS CAUSED BY A FOREIGN OBJECT, PROBABLY LOOSE BALL.  THIS CAN HAPPEN ANYTIME THE BALLNUT ASSY IS REMOVED FROM THE SCREWSHAFT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F    RTA16WE                        
20060502000032006050200003    2006       5          2          2006FA0000359    120060322G8011ES6462751       STARTER                                                                                                                                 ENGINE          TIGHT           B  WS9RK   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      NM07                                                                    STARTER TOO TIGHT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   
20060419001682006041900168    2006       4          19         2006FA0000360    420060314G6113D78115P         SPINNER                                 BEECH 58    58          1152740CE                                   MCAULY3AF32C3AF32C512   GL  ENGINE          CRACKED         C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP01                            TH2135                                  SPINNER HAS CRACKS IN 3 PLACES NEAR SCREW HOLES ADJACENT TO PROPELLER BLADES.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L72 3O      3A16            5  CP22EA    
20060418002192006041800219CE  2006       4          18         2006FA0000361    120060310G2910605700311       FLEX LINE                               LEAR  60    60LEAR      5170707CE                                                               HYD SYS         RUPTURED        D      A   UNSCHED LANDING                                                                                 KF FLUID LOSS                FLT CONT AFFECTED                                   CRCRUISE         1                      SW11898PA                       111                                     DURING FLIGHT, LOST NR 1 HYDRAULIC PRESSURE, DIVERTED INTO AIRPORT AND LANDED WITHOUT INCIDENT.  TROUBLESHOOT AND FOUND RUPTURED HYDRAULIC FLEX LINE, PN 605700311 WHICH IS MOUNTED ON THE PRESSURE SIDE OF THE HYDRAULIC EDP.  INSTALLED NEW HYDRAULIC FLEX LINE WITH PN 605700311.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F    RTA10CE                        
20060419001942006041900194EU  2006       4          19         2006FA0000362    120060314G6220C622A1002104    PLATE                                   UROCOPEC120 EC120B      8680987EU                                                               MAIN ROTOR HEAD UNBONDED        B  KW1RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA07453F 3429       M309        1205                                    LOWER DROOP RING WEAR PLATE BECAME UNBONDED AND CAME OFF THE MAIN ROTOR HUB.  THE ENTIRE PLATE WAS FOUND APPROXIMATELY 20 FT FROM THE AIRCRAFT.  IT IS NOT CLEAR WHETHER THE PART FELL OFF DURING ENGINE START UP OR SHUTDOWN.  WE BELIEVE THE UNBONDING TO BE THE RESULT OF THE DROOP RING STOPS COMING INTO CONTACT WITH THE WEARPLATE, DURING PERIODS OF TIME WHEN THE AIRCRAFT IS STATIC ON THE RAMP AND SUBJECT TO HIGH WINDS.  RECOMMEND SECURING THE MAIN ROTOR BLADES WHEN THE PREVAILING WINDS REACH 15 KNOTS.  (K)                                                                                                                                                                                                                    1G72 3U    NCR0001RD                      
20060418002212006041800221SO  2006       4          18         2006FA0000363    120060301G270062701100        CABLE                                   PIPER PA28  PA28R201    7102816SO  LYC   O360  IO360A1A    41514EA                              FUSELAGE        FRAYED          B  WIWRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP07962WW4810                   2844022                                 WHILE CONDUCTING AN ANNUAL INSPECTION PRIOR TO PLACING THE AIRCRAFT ONLINE AFTER PURCHASING IT FROM A LOCAL OPERATOR, BOTH FORWARD RUDDER CABLES WERE FOUND TO BE BADLY WORN AND FRAYED.  RESEARCH OF THE MAINTENANCE RECORDS SHOWED THAT THE PREVIOUS OWNERS HAD FAILED TO COMPLY WITH SB WHICH REQUIRES REPETITIVE INSPECTIONS OF ALL FLIGHT CONTROL CABLES.  THIS SB WAS APPLICABLE TO THIS AIRCRAFT.  (K)                                                                                                                                                                                                                                                                                                                                   1L71 3O3  O  2A13    1E10                 
20060419002042006041900204SO  2006       4          19         2006FA0000364    120060301G272062701124        CABLE                                   PIPER PA28  PA28R201    7102816SO  LYC   O360  IO360A1A    41514EA                              FUSELAGE        FRAYED          B  WIWRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP07962WW4810                   2844022                                 WHILE CONDUCTING AN ANNUAL INSPECTION PRIOR TO PLACING THE AIRCRAFT ONLINE AFTER PURCHASING IT FROM A LOCAL OPERATOR THE RT AILERON BALANCE CABLE WAS FOUND TO BE BADLY WORN AND FRAYED WITH ONLY A FEW STRANDS LT INTACT.  RESEARCH OF THE MAINTENANCE RECORDS SHOWED THAT THE PREVIOUS OWNERS HAD FAILED TO COMPLY WITH SB WHICH REQUIRES REPETITIVE INSPECTIONS OF ALL FLIGHT CONTROL CABLES.  THIS SB WAS APPLICABLE TO THIS AIRCRAFT.  (K)                                                                                                                                                                                                                                                                                                 1L71 3O3  O  2A13    1E10                 
20060419002052006041900205SO  2006       4          19         2006FA0000365    120060301G274062701103        CABLE                                   PIPER PA28  PA28R201    7102816SO  LYC   O360  IO360A1A    41514EA                              FUSELAGE        FRAYED          B  WIWRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP07962WW4810                   2844022                                 WHILE CONDUCTING AN ANNUAL INSPECTION PRIOR TO PLACING THE AIRCRAFT ONLINE AFTER PURCHASING IT FROM A LOCAL OPERATOR THE LT STABILATOR CABLE WAS FOUND TO BE BADLY WORN AND FRAYED WITH ONLY A FEW STRANDS LT INTACT.  RESEARCH OF THE MAINTENANCE RECORDS SHOWED THAT THE PREVIOUS OWNERS HAD FAILED TO COMPLY WITH SB WHICH REQUIRES REPETITIVE INSPECTIONS OF ALL FLIGHT CONTROL CABLES.  THIS SB WAS APPLICABLE TO THIS AIRCRAFT.  (K)                                                                                                                                                                                                                                                                                                      1L71 3O3  O  2A13    1E10                 
20060419002642006041900264SO  2006       4          19         2006FA0000366    120060301G274062701102        CABLE                                   PIPER PA28  PA28R201    7102816SO  LYC   O360  IO360A1A    41514EA                              FUSELAGE        FRAYED          B  WIWRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP07962WW4810                   2844022                                 WHILE CONDUCTING AN ANNUAL INSPECTION PRIOR TO PLACING THE AIRCRAFT ONLINE AFTER PURCHASING IT FROM A LOCAL OPERATOR THE RT FWD STABILATOR CABLE WAS FOUND TO BE BADLY WORN AND FRAYED.  RESEARCH OF THE MAINTENANCE RECORDS SHOWED THAT THE PREVIOUS OWNERS HAD FAILED TO COMPLY WITH SB  WHICH  REQUIRES REPETITIVE INSPECTIONS OF ALL FLIGHT CONTROL CABLES.  THIS SB WAS APPLICABLE TO THIS AIRCRAFT.  (K)                                                                                                                                                                                                                                                                                                                                  1L71 3O3  O  2A13    1E10                 
20060419002352006041900235SO  2006       4          19         2006FA0000367    120060301G274062701100        CABLE                                   PIPER PA28  PA28R201    7102816SO  LYC   O360  IO360A1A    41514EA                              FUSELAGE        FRAYED          B  WIWRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP07963PA5350                   2844023                                 WHILE CONDUCTING AN ANNUAL INSPECTION PRIOR TO PLACING THE AIRCRAFT ONLINE AFTER PURCHASING IT FROM A LOCAL OPERATOR THE LT FORWARD STABILATOR CABLE WAS FOUND TO BE BADLY WORN AND FRAYED.  THE AREA OF FRAYING WAS LOCATED UNDER THE REAR SEATS IN THE INSPECTION AREA AT THE REAR PULLEYS.  THIS IS A KNOWN AREA OF WEAR FOR ALL PA 28, 34, AND 44 MODEL AIRCRAFT.  RESEARCH OF THE MAINTENANCE RECORDS SHOWED THAT THE PREVIOUS OWNERS HAD FAILED TO COMPLY WITH SB WHICH REQUIRES REPETITIVE INSPECTIONS OF ALL FLIGHT CONTROL CABLES.  THIS SB WAS APPLICABLE TO THIS AIRCRAFT.  (K)                                                                                                                                                      1L71 3O3  O  2A13    1E10                 
20060419002882006041900288SO  2006       4          19         2006FA0000368    120060301G272062701100        CONTROL CABLE                           PIPER PA28  PA28R201    7102816SO  LYC   O360  IO360A1A    41514EA                              FUSELAGE        FRAYED          B  WIWRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP07963PA5350                   2844023                                 WHILE CONDUCTING AN ANNUAL INSPECTION PRIOR TO PLACING THE AIRCRAFT ONLINE AFTER PURCHASING IT FROM A LOCAL OPERATOR THE RT FWD RUDDER CABLE WAS FOUND TO BE BADLY WORN AND FRAYED.  THE LOCATION OF THE FRAYING WAS JUST UNDER THE CENTER CONSOLE FOR THE STABALATOR TRIM AND JUST AS IT EXITED IN TO THE INSPECTION AREA UNDER THE REAR SEATS AT THE FORWARD PULLEY.  THIS IS A KNOWN AREA OF WEAR FOR ALL PA 28, 34, AND 44 MODEL AIRCRAFT.  RESEARCH OF THE MAINTENANCE RECORDS SHOWED THAT THE PREVIOUS OWNERS HAD FAILED TO COMPLY WITH SB WHICH REQUIRES REPETITIVE INSPECTIONS OF ALL FLIGHT CONTROL CABLES.  THIS SB WAS APPLICABLE TO THIS AIRCRAFT.  (K)                                                                             1L71 3O3  O  2A13    1E10                 
20060419002792006041900279SO  2006       4          19         2006FA0000369    120060301G271062701123        CONTROL CABLE                           PIPER PA28  PA28R201    7102816SO  LYC   O360  IO360A1A    41514EA                              WING            FRAYED          B  WIWRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP07963PA5350                   2844023                                 WHILE CONDUCTING AN ANNUAL INSPECTION PRIOR TO PLACING THE AIRCRAFT ONLINE AFTER PURCHASING IT FROM A LOCAL OPERATOR THE LT AILERON BALANCE CABLE WAS FOUND TO BE BADLY WORN AND FRAYED.  THE LOCATION OF THE FRAYING WAS AT THE 1ST IB PULLEY IN THE WING ROOT.  THIS IS A KNOWN AREA OF WEAR FOR ALL PA 28, 34, AND 44 MODEL AIRCRAFT.  RESEARCH OF THE MAINTENANCE RECORDS SHOWED THAT THE PREVIOUS OWNERS HAD FAILED TO COMPLY WITH SB WHICH REQUIRES REPETITIVE INSPECTIONS OF ALL FLIGHT CONTROL CABLES.  THIS SB WAS APPLICABLE TO THIS AIRCRAFT.  (K)                                                                                                                                                                                   1L71 3O3  O  2A13    1E10                 
20060419002912006041900291SO  2006       4          19         2006FA0000370    120060301G271062701124        CONTROL CABLE                           PIPER PA28  PA28R201    7102816SO  LYC   O360  IO360A1A    41514EA                              WING            FRAYED          B  WIWRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP07963PA5350                   2844023                                 WHILE CONDUCTING AN ANNUAL INSPECTION PRIOR TO PLACING THE AIRCRAFT ONLINE AFTER PURCHASING IT FROM A LOCAL OPERATOR THE RT AILERON BALANCE CABLE WAS FOUND TO BE BADLY WORN AND FRAYED WITH ONLY 1 STRAND LEFT HOLDING IT TOGETHER.  THE LOCATION OF THE FRAYING WAS AT THE 1ST IB PULLEY IN THE WING ROOT.  THIS IS A KNOWN AREA OF WEAR FOR ALL PA 28, 34, AND 44 MODEL AIRCRAFT.  RESEARCH OF THE MAINTENANCE RECORDS SHOWED THAT THE PREVIOUS OWNERS HAD FAILED TO COMPLY WITH SB 1048 WHICH REQUIRES REPETITIVE INSPECTIONS OF ALL FLIGHT CONTROL CABLES.  THIS SB WAS APPLICABLE TO THIS AIRCRAFT.  (K)                                                                                                                                  1L71 3O3  O  2A13    1E10                 
20060419002992006041900299SO  2006       4          19         2006FA0000371    120060301G271062701099        CONTROL CABLE                           PIPER PA28  PA28R201    7102816SO                                                               LT WING         FRAYED          B  WIWRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP07962WW4810                   2844022                                 WHILE CONDUCTING AN ANNUAL INSPECTION PRIOR TO PLACING THE AIRCRAFT ON LINE AFTER PURCHASING IT FROM A LOCAL OPERATOR THE LT FORWARD AILERON BALANCE CABLE WAS FOUND TO BE BADLY WORN AND FRAYED.  RESEARCH OF THE MAINTENANCE RECORDS SHOWED THAT THE PREVIOUS OWNERS HAD FAILED TO COMPLY WITH SB 1048 WHICH REQUIRES REPETITIVE INSPECTIONS OF ALL FLIGHT CONTROL CABLES.  THIS SB WAS APPLICABLE TO THIS AIRCRAFT.  (K)                                                                                                                                                                                                                                                                                                                     1L71 3O      2A13                         
20060419002572006041900257SO  2006       4          19         2006FA0000372    120060309G32133948903         AXLE                                    PIPER PA34  PA34220T    7103420SO  CONT  O300  O300*       17022SO                              MLG             CRACKED         D  NTBRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM059219X                       3448038                                 CRACKS IN BOTH UPPER BOLT HOLES THAT SECURE AXLE TO STRUT ASSEMBLY ON BOTH LT AND RT MLG.  PROBABLE CAUSE MAYBE HARD LANDING OR FATIGUE CRACKS DO TO NORMAL USE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L72 3O3  O  A7SO    E253                 
20060420001202006042000120CE  2006       4          20         2006FA0000373    120060322G551004320049        BRACKET                                 CESSNA150   152         2071835CE  LYC   O235  O235*       41505EA                              HORIZONTAL STAB CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW1549053*                      15281124                                3 CRACKS WHERE FOUND ON THE TOP RT OB BOLT HOLE AND ONE CRACK IN WELD JUST AFT OF SAME BOLT HOLE, (NUT PLATES HAD BEEN PREVIOUSLY REMOVED).  UNKNOWN CAUSE, AD SHOULD BE REVISED TO REFER FURTHER INSPECTION OF COMPLETE BRACKET ASSY.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1H71 3O3  ONT3A19    E223                 
20060420001172006042000117SO  2006       4          20         2006FA0000374    120060403G27301159CS52093409  STOP                                    GULSTMGV    GULFSTREAMGV3980116SO  RROYCEBR700 BR700710A110     NE                              LT ELEVATOR     BROKEN          B  CW1RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA11780F 3750                   530                                     DURING SCHEDULED TAIL INSPECTION LT ELEVATOR UP AND DOWN STOP WAS FOUND BROKEN OFF AND LAYING IN ELEVATOR ATTACH/HINGE AREA.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F4  FRTA12EA   E00057EN             
20060420001712006042000171CE  2006       4          20         2006FA0000375    120060403G3397                CONNECTOR                               BEECH MU300 400A        1155402CE  PWA   JT15  JT15D5      52112NE                              WIRE HARNESS    WRONG PART      B  E81RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03493CW                       RK93                                    DURING SCHEDULED INSPECTION FOUND SEVERAL INCORRECT TYPE SPLICE CONNECTORS AND REPAIRS IN CABIN COLD CATHODE LIGHTING WIRING.  HAVE FOUND THIS TO BE THE APPARENT CAUSE OF MINOR FIRES AND OVERHEATING ABOVE THE HEADLINER IN SEVERAL AIRCRAFT PREVIOUSLY..  SEVERAL COMMUNIQUS HAVE NOTED THIS SUBJECT PREVIOUSLY.  SUGGEST A MANDATORY SB OR SAFETY COMMUNIQU BE ISSUED FOR A ONE TIME INSPECTION OF COLD CATHODE WIRING FOR NON-APPROVED CONNECTORS AND WIRING REPAIRS.  WARNINGS AND SPECIFIC REPAIR INSTRUCTIONS SHOULD BE ADDED TO THE MM.  (K)                                                                                                                                                                                         2H72 4F4  FRTA16SW   E25EA                
20060420001722006042000172CE  2006       4          20         2006FA0000376    120060330G561010138402518     WINDSHIELD                              BEECH B300  B300        1159232CE  PWA   PT6   PT6*        52043EA                              COCKPIT         CRACKED         B  E81RK   NONE                                                                                            O  OTHER                                                                         CRCRUISE         1                      GL0337TD 1236                   FL25                                    FLIGHT CREW REPORTED CO-PILOTS WINDSHIELD RAPIDLY FAILED IN CRUISE FLIGHT, INNER LAYER (SPIDER WEBBED) OVER ENTIRE INTERIOR SURFACE.  DELAMINATIONS NOTED SPREADING FROM BOTH IB CORNERS UPON REMOVAL.  TECH INSTALLING REPLACEMENT WINDSHIELD NOTED PREVIOUS INSTALLATION MAY HAVE HAD SEALS INSTALLED INCORRECTLY, CAUSING INCREASED STRESS ON WINDSHIELD ASSY.  RECOMMEND TECH INSTALLING REPLACEMENT WINDSHIELDS REVIEW CURRENT STRESS FREE INSTALL KIT INSTRUCTIONS AND MM INSTALL PROCEDURES CAREFULLY PRIOR TO INSTALLATION.  (K)                                                                                                                                                                                                        2L72 4T3  TRTA24CE   E2NE                 
20060420001742006042000174GL  2006       4          20         2006FA0000377    120060327G5552                ATTACH FITTING                          AMTR  ZENITHZENITHCH701 05611WIGL  ROTAX 912   ROTAX912    55555EU                              ELEVATOR HINGE  CRACKED         G      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL01701BX                       71514                                   DURING CONDITION INSPECTION IT WAS DISCOVERED THAT THE RT ELEVATOR HINGE ATTACH SUPPORT HAD A CRACK IN THE T/E RADIUS THAT WAS STOP DRILLED.  A DOUBLER REPAIR WAS INSTALLED.  THE ELEVATOR HORN ATTACH ALSO HAD A LOOSE RIVET.  THIS WAS REPAIRED BY INSTALLING AN HARDWARE.  CLOSE ATTENTION SHOULD BE PAID TO THESE AREA EVEN ON PREFLIGHT AS THIS IS THE THIRD KNOWN INCIDENCE OF THIS KIND IN THE AREA.  (K)                                                                                                                                                                                                                                                                                                                               1H71 3I3  INTEXPA1H71EXPE3I               
20060502000082006050200008    2006       5          2          2006FA0000378    120060329G8011MHB4016         STARTER                                                                                                                                                 MALFUNCTIONED   B  WS9RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM07                                                                    BENDIX DRIVE WOULD NOT DISENGAGE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    
20060420001602006042000160CE  2006       4          20         2006FA0000379    120060403G240010300B          ALTERNATOR                              CESSNA207   207         2073602CE                                                                               OVERTORQUED     B  UT2RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO09                                                                    PART RECEIVED O/H FROM STOCK.  NO CURRENT OUTPUT WHEN INSTALLED ON AIRCRAFT.  BENCH CHECKING RESULTED IN MALFUNCTION OF BRUSH BLOCK HARDWARE DUE TO POSSIBLE OVER TORQUING OF HARDWARE DURING ASSY.  COMPONENT WAS OVERHAULED BY CRS NR UT2R226L UNDER W/O NR M940120 DATED AUG 17, 2005, FORM TRACKING NR F082283.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                        1H71 3O      A16CE                        
20060420001802006042000180WP  2006       4          20         2006FA0000380    220060330G75103751160         FITTING                                 LEAR  35    35A         5170602CE  GARRTTTFE731TFE731*     01518WP                              TAIL            MISINSTALLED    B  BIORO   OTHER                                                                                           FI FLT CONT AFFECTED         FLT. ATTITUDE INST.                                 APAPPROACH       1                      EA23288JP                       288                                     AIRCRAFT EXPERIENCED HORIZONTAL STABILIZER STALL DURING APPROACH, DURING SEVERE ICING.  AIRCRAFT RECOVERED FROM STALL AND LANDING NORMAL.  INSPECTION OF TAIL DE-ICE SYSTEM FOUND BLEED AIR LEAKING IN AFT PART OF TAIL AT 90 DEGREE ELBOW.  DURING REMOVAL OF 90 DEGREE ELBOW IT WAS FOUND THAT THE WIGGINS SEALS WERE INSTALLED INCORRECTLY, UNABLE TO DETERMINE WHEN THIS FITTING WAS INSTALLED.  COULD HAVE COME FROM MFG DURING PRODUCTION.  HAS NOT BEEN CHANGED BY OWNER IN 11 YEARS.  TAIL AND WING HEAT FUNCTIONAL CHECKED NORMAL AT LAST INSPECTION.  NO INFO IN MM FOR INSTALLING THIS TYPE.  (K)                                                                                                                                    2L72 4F4  F  A10CE   E6WE                 
20060420002262006042000226CE  2006       4          20         2006FA0000381    120060324G3213054119810       STRUT                                   CESSNA172   172N        2072434CE  LYC   O360  O360*       41514EA                              MLG             BROKEN          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NE01739YA                       17270902    RL514576T                   LANDING GEAR BROKE JUST OUTSIDE OF THE GEAR BOLT.  THE FACE OF THE CRACKED AREA APPEARS TO HAVE RUST ON IT THAT COULD INDICATE A PREVIOUS CRACK.  (NE01200603823) (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1H71 3O3  ONT3A12    E286                 
20060512001262006051200126SO  2006       5          12         2006FA0000382    120060323G3320AL1235T422C27   LAMP                                    GULSTMGV    GV          3980116SO  RROYCEBR700 BR700710A110     NE                              GALLEY          INOPERATIVE     G      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM091KE  400                    574                                     DURING ROUTINE LAMP REPLACEMENT, IT WAS DISCOVERED THAT ONE END OF THE REMOVED UNIT WAS DISCOLORED.  THE DISCOLORATION WAS THOUGHT TO BE DUE TO OVERHEATING.  THE LOCATION OF THE FAILED LAMP WAS IN THE GALLEY OVERHEAD.  INSTALLED NEW UNIT OF SAME MFG AND PN.  OPERATIONAL CHECK, OK.  REPORTING THIS DUE TO CONCERN THAT THE OPERATION OF THIS LIGHT COULD RESULT IN A POSSIBLE FIRE CAUSED BY OVERHEATING OF THESE UNITS.  (K)                                                                                                                                                                                                                                                                                                            2L72 4F4  FRTA12EA   E00057EN             
20060424001842006042400184SO  2006       4          24         2006FA0000383    120060306G2140A23D04          REGULATOR       JANITROL                PIPER PA23  PA23250     7102308SO  LYC   O540  TIO540*     41532EA                              CABIN HEATER    LEAKING         B  GFVRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM136549A           8213015F    277954006                               AIRCRAFT RECEIVED FROM NEW OWNER WANTING HEATER MADE OPERATIONAL:  TOTALLY DEACTIVATED.  REPLACED HEATER ASSY DUE TO EXTREME DETERORATION.  FUEL REGULATOR REPLACED DUE TO LEAKAGE AND FAILURE TO REGULATE.  FOUND INLET PORT PARTIALLY PLUGGED BY CORROSSION BY-PRODUCTS AND REMNANTS OF DAMAGED THREADS.  N/E REPAIRABLE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                1L72 3O3  O  1A10    E14EA                
20060424001352006042400135CE  2006       4          24         2006FA0000384    120060327G3230101810151       BOLT                                    BEECH 300   300BEECH    1152930CE                                                               RT GEAR DRAG LEGMISDRILLED      D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15810N                        FL419                                   THIS IS AN ALEMITE TYPE BOLT.  IT WAS FOUND THAT GREASE WAS NOT GETTING TO THE BUSHINGS ON THE FAR END OF THE BOLT.  UPON EXAMINATION, IT WAS FOUND THAT THE CENTER GREASE PORT IN THE BOLT WAS NOT DRILLED FAR ENOUGH TO ALLOW GREASE TO GET TO THE FINAL SIDE-DRILLED PORT.  THUS THE BUSHING FOR THAT PORT WAS NOT GETTING LUBRICATION.  DRAG LINKS WITH THIS PN BOLT SHOULD BE CHECKED FOR PROPER LUBRICATION.  (K)                                                                                                                                                                                                                                                                                                                         2L72 4T      A24CE                        
20060424001742006042400174SO  2006       4          24         2006FA0000385    220060331G8530                CYLINDER HEAD                           CESSNA414   414A        2075907CE  CONT  O520  TSIO520BB   17040SO                              RT ENG          SEPARATED       D      K   NONE                                                                                            E  VIBRATION/BUFFET                                                              CRCRUISE         1                      SO15414AM                       414A0850    287566R                     DURING FLIGHT, VIBRATION WAS NOTED ON RT ENGINE.  INSPECTED ENGINE AND FOUND NR 6 CYLINDER SEPARATED WHERE BARREL MEETS HEAD.  PROBABLE CAUSE: UNKNOWN.  RECOMMENDATIONS:  THIS IS AN ECI CYLINDER.  REFERENCE NEEDS TO BE MADE TO THEM TO RESOLVE THE PROBLEM.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L72 3O3  O  A7CE    E8CE                 
20060424001452006042400145SO  2006       4          24         2006FA0000386    120060405G2121553002          COOLING FAN                             PIPER PA23  PA23250     7102308SO  LYC   O540  IO540*      41532EA                              INST PANEL      BURNED          B      E   ENGINE SHUTDOWN                                                                                 BA SMOKE/FUMES/ODORS/SPARKS  FLAME/FIRE                                          TXTAXI/GRND HDL  1                      EA2352WW 6112                   278154014                               AFTER STARTING ENGINES, THE PILOT SMELLED SMOKE AND OBSERVED FLAMES BEHIND CO-PILOTS INSTRUMENT PANEL.  ENGINES WERE SHUTDOWN.  WHEN MASTER SWITCH WAS TURNED OFF, THE FLAME WENT OUT.  INVESTIGATION REVEALED THAT THE AVIONICS COOLING FAN HAD CAUGHT FIRE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L72 3O3  O  1A10    1E4                  
20060424001822006042400182CE  2006       4          24         2006FA0000387    120060328G3040260148830       DEICE SYSTEM                            CESSNA208   208B        2073701CE                                                               WINDSHIELD      LEAKING         C      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA21208JH                       208B1144                                WATER LEAKS AROUND/THROUGH EDGE SEAL OF WINDSHIELD DE-ICE HOT PLATE AND OBSTRUCTS FORWARD VIEW OF PILOT.  THIS WATER FREEZES BETWEEN THE HOT PLATE AND THE WINDSHIELD.  IN RAIN CONDITIONS WITH TEMPERATURE ABOVE FREEZING WATER ACCUMULATES AND FILLS 4 TO 5 INCHES OF THE LOWER PORTION OF THE HOT PLATE.  THIS WATER FLOATS AROUND THE IN THE LAYER BETWEEN THE HOT PLATE AND THE WINDSHIELD MAKING LANDING THE AC VERY DANGEROUS FROM THE PILOTS SEAT.  IN TEMPERATURES BELOW FREEZING THIS WATER FREEZES AND COMPLETELY BLOCKS THE PILOTS FORWARD VIEW.  THIS IS THE SECOND HOT PLATE TRIED ON THIS NEW AIRCRAFT WITH TWO DIFFERENT EDGE SEAL CONFIGURATIONS.  THE WINDSHIELD DEICE HOT PLATE HAS BEEN REMOVED FROM THIS AC FOR SAFETY.    1H71 3T      A37CE                        
20060424001532006042400153SO  2006       4          24         2006FA0000388    120060307G551189T20543        RIB             GRUMAN                  GRUMAVS2    S2F         3951006SO  GARRTTTPE331TPE331*     01514WP                              RT HORIZ STAB   CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP25448DF           N11140      152347                                  DURING MAINTENANCE ON THE RT SIDE HORIZONTAL STABILIZER, CRACKS WERE ON 2 RIB SECTIONS.  CRACKS WERE DETECTED ON RIBS PN 89T920543, STA 138.858 AND PN 89T1029-1, STA 80.608.  THESE CRACKS WERE FOUND ON THE UPPER FWD LEADING EDGE TABS WHERE THE RIB ATTACHES TO THE HORIZONTAL STAB SKIN.  RIBS WERE REPAIRED IAW THE STRUCTURAL REPAIR MANUAL.  (K)                                                                                                                                                                                                                                                                                                                                                                                        2H72 4O3  TRTEXPA2H72E2WE                 
20060424001552006042400155CE  2006       4          24         2006FA0000389    120060128G323212810281        ACTUATOR        CESSNA                  CESSNA210   210L        2073448CE  CONT  O550  IO550*           SO  MCAULYD3A34 D3A34C402   GL  RT MLG DOOR     FAILED          G      O   OTHER                                                                                           J  WARNING INDICATION                                                            LDLANDING        1                      EA114FL  5258 15    4486        21061382    289006R     921108          MECHANICAL FAILURE OF THE RT MLG DOOR ACTUATOR, PREVENTED THE EXTENSION OF THIS AC LANDING GEAR EITHER BY NORMAL OF EMERGENCY PROCEDURES.  THE FAILURE WAS THE ACTUATOR GLAND AND CIRCLIP COMING APART FROM THE ACTUATOR.  THE RT MLG ACTUATOR WAS REMOVED AND RESEALED BY A LOCAL MAINTENANCE FACILITY ON 9/24/2004 AT 343.8 HOURS TACH 14.7 HOURS SINCE RESEAL.  INVESTIGATION OF THIS INCIDENT WAS INCONCLUSIVE OF WHAT CAUSED THIS FAILURE.  (K)                                                                                                                                                                                                                                                                                            1H71 3O3  O  3A21    E3SO    5  CP47GL    
20060424002272006042400227SO  2006       4          24         2006FA0000390    120060320G256045402           HARNESS                                 PIPER PA28  PA28161     7102803SO                                                               SHOULDER HARNESSFAILED          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA172203T50                     287916300                               HAVE HAD NUMEROUS PROBLEMS WITH PACIFIC SCIENTIFIC INERTIA REELS, PN 1107447-29,  MFG PN 564-863 (PS50039-4-49).  THESE HARNESSES DO NOT RETURN AND/OR DO NOT FUNCTION UNDER A SUDDEN LOAD.  ON OCCASION, HAVE FOUND THEM BAD STRAIGHT OUT OF THE BOX.  THEY ARE ALSO VERY SUSCEPTABLE TO WARPAGE/ MALFUNCTION UPON INSTALLATION.  (K)                                                                                                                                                                                                                                                                                                                                                                                                          1L71 3O      2A13                         
20060424002282006042400228SO  2006       4          24         2006FA0000391    120060329G324616403506        BRAKE DISC      CLEVELAND               PIPER PA31  PA31        7103102SO  LYC   O540  TIO540A2B   41532EA  MCAULY3DF36CB3DF36C526  GL  WHEEL           CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE019007Y                       3111        R47161      981497          FOUND CRACK IN BRAKE DISC ON OUTER EDGE. CRACK STARTED ON THE (P) IN PARKER FROM THE STAMPED NAME, MODEL, DATE, AND SN.  WHEN STAMPED COULD HAVE CAUSED A STRESS CRACK.  THE USE OF AN INK STAMP WOULD NOT CAUSE ANY STRESS ON THE DISC. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L72 3O3  O  A20SO   E14EA   5  C         
20060424002292006042400229SO  2006       4          24         2006FA0000392    220060410G74146310            MAGNETO                                 CESSNA206   U206F       2073333CE  CONT  O520  IO520F      17032SO                              ENGINE          CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NE058411Q348                    U20603271                               CHECKING ENGINE FOR PERSISTENT OIL LEAK, FOUND IT TO BE COMING FROM AREA OF LT MAG.  MAG REMOVED AND WAS FOUND TO HAVE 1.5 INCH SECTION OF MOUNTING FLANGE CRACKED OFF.  THIS IS THE SECOND MAG ON THIS ENGINE TO HAVE THIS PROBLEM.  PREVIOUS MAG WAS TORQUED TO SPECS AS WAS THIS ONE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3O3  O  A4CE    E5CE                 
20060502000072006050200007    2006       5          2          2006FA0000393    120060411G2434ALU1003         HOUSING                                                                                                                                 ENGINE          WORN            B  KC2RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03                                                                    THIS ALTERNATOR HAS -0- HOURS TIME-IN-SERVICE.  DURING INSPECTION, PRIOR TO SALE, IT WAS DISCOVERED THAT THE ROTOR HAD EXCESSIVE LATERAL MOVEMENT AS A RESULT OF EXCESSIVE WEAR OF THE DRIVE END HOUSING BEARING BORE.  THIS CONDITION WOULD HAVE LEAD TO PREMATURE FAILURE OF THE DRIVE GEAR/ALTERNATOR AND COULD HAVE LEAD TO A COMPLETE ENGINE FAILURE.  HAVE SEEN THIS SAME PROBLEM IN A VERY LARGE PERCENTAGE OF THESE ALTERNATORS RETURNED TO SERVICE BY OVERHAULER.  (K)                                                                                                                                                                                                                                                                                                           
20060425001292006042500129SO  2006       4          25         2006FA0000394    120060401G575142972           SPAR                                    PIPER J3    J3C*               SO                                                               AILERON         CORRODED        D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NE02                                                                    AILERON SPARS FOUND EXCESSIVE CORROSION UNDER ALL 3 HINGES.  NEEDED TO REPLACE SPAR ON BOTH LT AND RT AILERONS BEFORE RECOVERING AILERONS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1H71 3O      ATC660                       
20060424002352006042400235CE  2006       4          24         2006FA0000397    120060209G5753052390134       FLAP                                    CESSNA182   T182        2072736CE  LYC   O540  O540L3C5    41532EA                              RT WING         DAMAGED         D  AVXRK   NONE                                                                                            F  FLT CONT AFFECTED                                                             CRCRUISE         1                      NE015464N                       18267735    L2248140A                   ON DEC 4, 2005, THE RT FLAP JAMMED AT THE IB ATTACH ARMS IN ABOUT THE 20 DEGREE POSITION.  FLAP MOTOR CONTINUED TO RUN FOR A SHORT PERIOD OF TIME, CAUSING SEVERE DAMAGE AND DISTORTION TO THE JAMMED FLAP,  THE PILOT WAS ABLE TO LAND THE AIRPLANE WITHOUT FURTHER INCIDENT.  INSPECTION REVELED THAT THE TIP OF THE RT IB FLAP SUPPORT ARM CAME IN CONTACT WITH A BRACKET ON THE FLAP TRACK RIB ASSY CAUSING THE FLAP TO BIND.  REPAIRED BY REPLACING THE RT FLAP INCLUDING ALL THE ROLLERS AND BY REPLACING BOTH BRACKETS ON THE IB FLAP TRACK RIB ASSY.  (K)                                                                                                                                                                               1L71 3O3  O  3A13    E295                 
20060427002072006042700207CE  2006       4          27         2006FA0000398    120060327G5346051313211       BRACKET         CESSNA                  CESSNA175   175         2072502CE                                                               ENGING MOUNT    CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE077259M3822                   55559                                   FOUND THE UPPER LEFT ENGINE MOUNT BRACKET, P/N 0513132-11 IN THE 0513132-3 UPPER ENGINE MOUNT STRINGER CRACKED THROUGH THE BRACKET AROUND THE RADIUS OF THE WASHER.  INSPECTION WAS ACCOMPLISHED DUE TO NUMEROUS REPORTS OF THE SAME CONDITION FOUND ON LIKE MODELS OF AIRCRAFT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                1H71 3O    NT3A17                         
20060427002282006042700228CE  2006       4          27         2006FA0000399    120060327G7120051313211       BRACKET         CESSNA                  CESSNA175   175         2072502CE                                                               ENGINE MOUNT    CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE077259M3822                   55559                                   FOUND THE UPPER RIGHT ENGINE MOUNT BRACKET, P/N 0513132-11 IN THE 0513132-4 UPPER ENGINE MOUNT STRINGER, CRACKED.  INSPECTION WAS ACCOMPLISHED DUE TO NUMEROUS REPORTS OF THE SAME CONDITION FOUND ON LIKE MODELS OF AIRCRAFT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H71 3O    NT3A17                         
20060512000472006051200047SO  2006       5          12         2006FA0000400    120060106G2824236405492189    VALVE                                   PIPER PA34  PA34200T    7103406SO                                                               FUEL SYS        LEAKING         D      K   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      WP05                                                                    FUEL COULD NOT BE SHUT OFF AND FUEL WAS CROSS-FEEDING. SEVERAL CROSSFEED VALVES HAVE BEEN EXAMINED AND FOUND TO HAVE DEFECTIVE SEALS. O-RINGS WERE DISSOLVED AND RESEMBLED A TAR LIKE SUBSTANCE. IF THERE IS AN ENGINE FIRE OR LEAK, FUEL CANNOT BE SHUT OFF WHICH CREATES A SAFETY OF FLIGHT CONDITION THAT MUST BE CORRECTED.                                                                                                                                                                                                                                                                                                                                                                                                                 1L72 3O      A7SO                         
20060510002472006051000247CE  2006       5          10         2006FA0000401    120060425G555304311481        FITTING         CESSNA                  CESSNA150   152         2071835CE                                                               VERTICLE STAB   CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP2348968                       15281080                                PART ATTACHES VERTICLE STABILIZER SPAR TO THE HORIZONTAL STABILIZER SPAR ATTACH FITTING P/N 0432004-9(THIS FITTING HAS BEEN THE SUBJECT OF AD 80-11-04 AND SEB 3-06)PROBABLE CAUSE IS HIGH ACTT. AGING AIRCRAFT REQUIRE DILIGENT INSPECTIONS. (REF FAA HANDBOOK"BEST PRACTICES GUIDE FOR MAINTAINING AGING GENERAL AVIATION AIRCRAFT.                                                                                                                                                                                                                                                                                                                                                                                                           1H71 3O    NT3A19                         
20060510002482006051000248CE  2006       5          10         2006FA0000402    120060425G555304311481        FITTING         CESSNA                  CESSNA150   152         2071835CE                                                               VERTICLE STAB   CRACKED         B  N2YRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP2348968                       15281080                                PART ATTACHES VERTICAL STABILIZER SPAR TO THE HORIZONTAL STABILIZER SPAR ATTACH FITTING P/N 0432004-9(THIS FITTING HAS BEEN THE SUBJECT OF AD 80-11-04 AND SEB 3-06)PROBABLE CAUSE IS HIGH ACTT. AGING AIRCRAFT REQUIRE DILIGENT INSPECTIONS. (REF FAA HANDBOOK"BEST PRACTICES GUIDE FOR MAINTAINING AGING GENERAL AVIATION AIRCRAFT. AIRCRAFT TOTAL TIME IS 12,762.1                                                                                                                                                                                                                                                                                                                                                                           1H71 3O    NT3A19                         
20060426001162006042600116NM  2006       4          26         2006FA0000403    120060419G57402000610102501   BRACKET                                 PIPER PA60  PA60600     7106001NM                                                               RIGHT WING      CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NE0378LS 2177                   600546176                               FWD WING ATTACHMENTS, LEFT & RIGHT WINGS, FWD & AFT BRACKETS WERE NEVER RIVETED TO TOP & BOTTOM WING SKINS & INBOARD RIB FLANGES ALLOWING ALL LOADING TO BE TAKEN BY BRACKET FLANGES & INBD WING RIBS. ALL 4 BRACKETS ARE CRACKED. PICTURES AVAILABLE.  IT SEEMED MORE THAN COINCIDENTAL TO ME THAT THE FOUR RIVETS NEEDED TO ATTACH THE WING SKIN TO THE RIB AND THE ATTACHMENT BRACKET WERE MISSING ON BOTH WINGS, TOP AND BOTTOM. PERHAPS THERE WAS A MISTAKE ON THE ASSEMBLY DRAWING AT THE TIME OF MANUFACTURE. THE HOLES WERE NEVER EVEN DRILLED FOR THE RIVETS. THE AIRCRAFT WAS MANUF. IN 1978, 4 NEWER MODELS WERE INSPECTED AND FOUND TO BE CORRECTLY ASSEMBLED. PICTURES PROVIDED.                                                   1M72 3O    RTA17WE                        
20060511002972006051100297CE  2006       5          11         2006FA0000404    120060331G325059420011        BELLCRANK                               CESSNA340   340A        2076405CE                                                               NLG STEERING    CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL25340JY4544                   340A0979                                DURING ANNUAL INSPECTION FOUND NOSE GEAR STEERING BELLCRANK ASSY #5942001-1 CRACKED LEFT AND RIGHT SIDES AT PIVOT RADIOUS. NEW REPLACEMENT PART WITH SAME PART NUMBER OBTAINED FROM CESSNA AIRCRAFT IS MADE MUCH HEAVIER WITH ADDITIONAL MATERIAL IN CRACK PRONE AREA.  PART FAILURE COULD LEAD TO LOSS OF NOSE GEAR STEERING CONTROL.                                                                                                                                                                                                                                                                                                                                                                                                          1L72 3O      3A25                         
20060511002992006051100299CE  2006       5          11         2006FA0000405    120060331G325059420011        BELLCRANK                               CESSNA340   340A        2076405CE                                                               NLG STEERING    CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05340JY4544                   340A0979                                DURING ANNUAL INSPECTION FOUND NOSE GEAR STEERING BELLCRANK ASSY #5942001-1 CRACKED LEFT AND RIGHT SIDES AT PIVOT RADIOUS. NEW REPLACEMENT PART WITH SAME PART NUMBER OBTAINED FROM CESSNA AIRCRAFT IS MADE MUCH HEAVIER WITH ADDITIONAL MATERIAL IN CRACK PRONE AREA.  PART FAILURE COULD LEAD TO LOSS OF NOSE GEAR STEERING CONTROL.                                                                                                                                                                                                                                                                                                                                                                                                          1L72 3O      3A25                         
20060512000492006051200049    2006       5          12         2006FA0000406    420060314G3452                TRANSPONDER                             CESSNA680   680CE       2076811CE  PWA   306   PW306B           NE                              COCKPIT         MALFUNCTIONED   C      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      SO352428                        6800046                                 DEPARTED AND WAS TOLD BY DEPARTURE CONTROL THEY DID NOT HAVE A TARGET ON US.  SWITCHED TO SECOND TRANSPONDER WITH SAME RESULT.  BOTH TRANSPONDERS APPERARED TO BE IN NORMAL OPS.  LANDED AT AND WENT TO A BLACK AIRCRAFT(COMPLETE SHUTDOWN).  RESTARTED AND ALL WAS NORMAL DURING NEXT LEG.  DOWNLOADED COMPUTERS ON POST FLIGHT AT HOME BASE AND FOUND NO FAULTS.  HAVE FLOWN 49 LEGS SINCE THE OCCURANCE AND HAVE HAD NO FAILURES.                                                                                                                                                                                                                                                                                                            2L72 4F4  FRCT00012WIE35NE                
20060518001752006051800175SO  2006       5          18         2006FA0000407    120060414G1410LW18724         HOSE            LYC         TIO540AH1A  PIPER PA32  PA32R301T   7103220SO  LYC   O540  TIO540S1AD  41532EA                              ENGINE          DETERIORATED    B  UXCRA   UNSCHED LANDING                                                                                 R  PARTIAL RPM/PWR LOSS                                                          CRCRUISE         1                      SW05126LM                       3257336     L1146461A                   PARTIAL POWER LOSS, TWO CYLINDERS DROPPED OUT, CAUSED BY SMALL PARTICLES OF RUBBER HOSE FROM UPPER DECK AIR REFERENCE LINES FLAKING OFF AND OCCLUDING THE FUEL INJECTORS                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L71 3O3  O  A3SO    E14EA                
20060518002432006051800243SO  2006       5          18         2006FA0000408    120060329G323067146004        DRAG LINK                               PIPER PA44  PA44180     7104402SO                                                               NLG             FRACTURED       B      K   NONE                                                                                            O  OTHER                                                                         LDLANDING        1                      SO15938ER620  27                4496200                                 DURING LANDING, THE NOSE GEAR RETRACT DRAG BRACE FAILED AT THE PIVOT POINT. THE NOSE GEAR COLLAPSED AND THE AIRCRAFT VEERED OFF OF THE RUNWAY STRIKING A LARGE RUNWAY SIGN WITH THE RT OB WING SECTION. THE CAUSE OF THE FAILURE IS STILL UNDER INVESTIGATION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L72 3O      A19S0                        
20060518002442006051800244SO  2006       5          18         2006FA0000409    120060329G323067146004        DRAG LINK                               PIPER PA44  PA44180     7104402SO                                                               ZONE 700        FRACTURED       B      K   NONE                                                                                            O  OTHER                                                                         LDLANDING        1                      SO15938ER620  27                4496200                                 DURING LANDING, THE NOSE GEAR RETRACT DRAG BRACE (PN-67146-004) FAILED AT THE PIVOT POINT. THE NOSE GEAR COLLAPSED AND THE AIRCRAFT VEERED OFF OF THE RUNWAY STRIKING A LARGE RUNWAY SIGN WITH THE RT OB WING SECTION.  THE CAUSE OF THE FAILURE IS STILL UNDER INVESTIGATION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L72 3O      A19S0                        
20060518002552006051800255CE  2006       5          18         2006FA0000410    120060406G712007516001        MOUNT                                   CESSNA182   182Q        2072732CE  CONT  O470  O470U       17026SO                              ENGINE          CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO057551S2290                   18265200    286916R                     DURING ANNUAL INSPECTION THE LT AFT ENGINE MOUNT P/N 0751600-1 WAS FOUND CRACKED THRU THE ENGINE MOUNT BOLT AREA.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1H71 3O3  ONT3A13    E273                 
20060518002572006051800257CE  2006       5          18         2006FA0000411    120060406G2760632550033       LUG                                     CESSNA525   525A        2076615CE                                                               SPEED BRAKE     MISDRILLED      B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL0320GP 445                    525A0131                                AC WAS IN FOR A PHASE 1 AND 2 INSPECTION.  A BROKEN BONDING STRAP AT THE UPPER LT SPEEDBRAKE DOOR NECESSITATED REMOVAL OF THE BOLT CONNECTING THE PUSH ROD TO THE UPPER DOOR LUG.  DURING BOLT REMOVAL THE HELICOIL INSERT CAME OUT WITH THE BOLT AND WAS DEFORMED.  PROPER INSERTION OF A NEW HELICOIL WAS UNSUCCESSFUL AS THE BOLT WOULD NOT THREAD INTO IT.  A COUPLE OF ATTEMPTS INSUED AND DETERMINATION WAS MADE THAT THE HOLE WAS NOT PROPERLY DRILLED AND TAPPED TO ACCEPT THE HELICOIL.  MAINTENANCE SUPPORT HOTLINE REPRESENTATIVE AGREED WITH THE ASSESSMENT AND PROVIDED TECHNICAL DATA TO REMOVE THE UPPER DOOR LUG, BACK DRILL AND TAP TO THE PROPER SIZE.  INSTALLATION OF THE HELICOIL WAS THEN SUCCESSFUL.                     1L71 4F    RTA1WI                         
20060522002342006052200234SO  2006       5          22         2006FA0000412    220060424G85206416311052      THRU BOLT                               CESSNA188   A188B       2073005CE  CONT  O550  IO550*           SO  HARTZLHCC3Y HCC3YF1     GL  ENGINE          BROKEN          D      K   NONE                                                                                            D  INFLIGHT SEPARATION                                                           AGAGRICULTURE    1                      NM094918R200                    18802435T   284455R     EC1151A         THE ENGINE CRANKCASE THRU-BOLT BROKE. THIS THRU-BOLT IS LOCATED UNDER THE TOP OF THE OIL COOLER ADAPTER PLATE THRU TO THE NR 6 CYL TOP FRONT. IT BROKE OFF FLUSH AT THE CYL BASE WHILE IN FLIGHT. THE BOLT END WHICH BROKE OFF WITH THE CYL BASE NUT FLEW OUT THE FRONT OF THE COWL, PUT A GOUGE IN THE FACE OF THE PROP BLADE AND THEN HIT THE TOP OF THE COWL LEAVING A LARGE DENT. WHEN IT BROKE, THE OPPOSITE END OF THE BOLT WAS FORCED BACK AGAINST THE OIL COOLER ADAPTER PLATE AND DEFORMED THE PLATE. THIS THRU-BOLT IS A REPLACEMENT INSTALLED LAST AUGUST 2005 DUE TO THE ORIGINAL THRU-BOLT, 650 HRS SINCE REMAN, ALSO BREAKING AT THE SAME LOCATION. A NEW CYL BASE NUT HAD BEEN USED AND TORQUED TO 800 INCH LBS IAW SB96-7C.     1L71 3O3  O  A9CE    E3SO    5  CP25EA    
20060512001532006051200153SO  2006       5          12         2006FA0000413    120060427G8011MZ6222          DRIVE ASSY                              PIPER PA23  PA23160     7102304SO  LYC   O320  O320B1A     41508EA                              STARTER         FAILED          D      K   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      SW013326P152                    231277                                  STARTER DRIVE FAILED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L72 3O3  O  1A10    E274                 
20060512001542006051200154SO  2006       5          12         2006FA0000414    120060427G8011MZ6222          DRIVE ASSY                              PIPER PA23  PA23160     7102304SO  LYC   O320  O320B1A     41508EA                              STARTER         FAILED          D      K   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      SW013326P152                    231277                                  STARTER DRIVE FAILED                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L72 3O3  O  1A10    E274                 
20060530001692006053000169SO  2006       5          30         2006FA0000415    120060425G272131731           CABLE                                   MAULE MX7   MX7180      5460185SO                                                               RUDDER          FRAYED          G      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL2745829                                                               FOUND RIGHT AND LEFT RUDDER TRIM CABLE BADLY FRAYED AS THE CABLE EXISTED THE RUDDER SKIN.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3O    NC3A23                         
20060530001702006053000170CE  2006       5          30         2006FA0000416    120060425G555304311481        FITTING         CESSNA                  CESSNA150   152         2071835CE                                                               RUDDER          CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP2348968                       15281080                                PART ATTACHES VERTICLE STABILIZER SPAR TO THE HORIZONTAL STABILIZER SPAR ATTACH FITTING P/N 0432004-9(THIS FITTING HAS BEEN THE SUBJECT OF AD 80-11-04 AND SEB 3-06)PROBABLE CAUSE IS HIGH ACTT. AGING AIRCRAFT REQUIRE DILIGENT INSPECTIONS. (REF FAA HANDBOOK"BEST PRACTICES GUIDE FOR MAINTAINING AGING GENERAL AVIATION AIRCRAFT. AIRCRAFT TOTAL TIME IS 12,762.1                                                                                                                                                                                                                                                                                                                                                                           1H71 3O    NT3A19                         
20060613002112006061300211SO  2006       6          13         2006FA0000417    220060329G8530                PACKING                                 CESSNA402   402C        207590RCE  CONT  O520  TSIO520VB   17040SO                              ENGINE          OUT OF POSITION E      E   ENGINE SHUTDOWN                                                                                 K  FLUID LOSS                                                                    CRCRUISE         1                      SW99                                                                    #1 CYLINDER EXHAUST PUSHROD HOUSING PACKING BLEW OUT.  SUSPECT POSSIBLE CRANKCASE PRESSURIZATION.  PACKING HAD SMALL CUT MOST LIKELY FROM INSTALLATION HOWEVER THAT SOULD NOT HAVE ALLOWED IT TO BLOW OUT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L72 3O3  O  A7CE    E8CE                 
20060518002412006051800241SO  2006       5          18         2006FA0000418    120060422G32136703704         STRUT                                   PIPER PA44  PA44180T    7104404SO                                                               LT MLG          BROKEN          C      K   NONE                                                                                            O  OTHER                                                                         TXTAXI/GRND HDL  1                      NM03838PC                       448107056                               LT GEAR STRUT BROKE AT HOUSING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L72 3O      A19SO                        
20060518002422006051800242SO  2006       5          18         2006FA0000419    120060422G32136703704         STRUT                                   PIPER PA44  PA44180T    7104404SO                                                               LT MLG          BROKEN          D      K   NONE                                                                                            O  OTHER                                                                         TXTAXI/GRND HDL  1                      NM03838PC                       448107056                               LH MLG STRUT BROKE ON TAXI                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L72 3O      A19SO                        
20060510001392006051000139CE  2006       5          10         2006FA0000420    120060414G246050369101163     BUSS BAR        BEECH                   BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6*        52043EA                              RT WING         CORRODED        B  E81RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03968T                        BB570                                   DURING SCHEDULED INSPECTION FOUND EXCESSIVE CORROSION ON RT WS 54.80 WEB HOT BATTERY BUS PANEL BUS BAR AND FUSE HOLDERS, REQUIRING COMPONENT REPLACEMENT.  AIRCRAFT PREVIOUSLY MODIFIED WITH SEALED LEAD-ACID BATTERY.  HAVE NOTED SIMILAR CORROSION ISSUES ON OTHER OLDER AC MODIFIED WITH LEAD-ACID BATTERY INSTALLATIONS.  RECOMMEND THAT AREAS ADJACENT TO THE BATTERY BOX SHOULD BE INSPECTED CAREFULLY FOR CORROSION EACH SCHEDULED PHASE INSPECTION, ESPECIALLY THE ELECTRICAL SYSTEM COMPONENTS, FOR AIRCRAFT RETROFITTED WITH LEAD-ACID BATTERIES.  (K)                                                                                                                                                                                1L72 4T3  T  A24CE   E2NE                 
20060511000982006051100098CE  2006       5          11         2006FA0000421    120060410G1430MS27039109      SCREW           BEECH                   BEECH MU300 400A        1155402CE                                                               FLOOR PANEL     WRONG PART      B  E81RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03907JE                       RK107                                   DURING INSPECTION IAW MFG SB, FOUND BRAKE HYDRAULIC LINE DAMAGED BY FLOOR PANEL ATTACHING SCREW.  REPAIRED TUBING AND MODIFIED FLOOR PANELS IAW SB.  HAVE FOUND THIS SAME CONDITION ON OTHER AIRCRAFT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2H72 4F    RTA16SW                        
20060511002002006051100200CE  2006       5          11         2006FA0000422    120060410G361045A6351771      TUBE                                    BEECH MU300 400A        1155402CE                                                               BLEED AIR SYS   BROKEN          B  E81RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03907JE5113                   RK107                                   DURING RECURRING 400 HR INSPECTION REQUIRED BY AD, FOUND AFT FUSELAGE RT BLEED AIR DUCT ASSY.  BELLOWS BRAIDED WIRE MESH BLOWN OUT OF END FITTINGS.  SUSPECTED TO BE CAUSED BY BLEED AIR LEAK FROM EITHER CRACKED BELLOWS OR FATIGUE/TUBING MIS-ALIGNMENT STRESS.  REPLACED TUBE ASSY WITH SUPERSEDING (PN 45A63517-075) TUBE ASSY.  RECOMMEND POSSIBLE AFT FUSELAGE BLEED AIR TUBING OF OLDER PN`S HAVE A 5000 HR LIFE LIMIT.  (K)                                                                                                                                                                                                                                                                                                             2H72 4F    RTA16SW                        
20060512001422006051200142CE  2006       5          12         2006FA0000423    120060419G32301698200111      DRAG BRACE                              BEECH 23    A24R        1151252CE  LYC   O360  IO360A1A    41514EA                              NLG             BROKEN          G      K   NONE                                                                                            O  OTHER                                                                         LDLANDING        1                      GL138015R2111                   MC54                                    THE AIRCRAFT TOUCHED DOWN  UNEVENTFUL.  DURING ROLLOUT, THE NOSE GEAR COLLAPSED ABOUT 1500 FT AFTER TOUCHDOWN.  THE DRAG BRACE FAILED AT THE YOKE WHERE IT ATTACHES TO THE NOSE GEAR.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L71 3O3  O  A1CE    1E10                 
20060510002262006051000226CE  2006       5          10         2006FA0000425    120060417G8011S539800M30      SPRING                                  CESSNA182   182H        2072718CE  CONT  O470  O470R       17026SO                              STARTER         BROKEN          G      K   NONE                                                                                            O  OTHER                                                                         TXTAXI/GRND HDL  1                      CE018503S           S1475691    18256603    1317375R4                   STARTER DRIVE WAS OVERHAULED BY A CERTIFIED REPAIR STATION.  (PN S539800M30) STARTER ADAPTER SPRINGS WERE INSTALLED IAW STC DURING THE OVERHAUL.  THE STARTER WAS INSTALLED ON THIS ENGINE AND WAS OPERATED FOR 4.06 HOURS (5 STARTS) BEFORE IT FAILED.  AN INSPECTION OF THE STARTER DRIVE ADAPTER FOUND THE STARTER ADAPTER SPRING WAS BROKEN AND DEFORMED.  THE INTERNAL PARTS WERE DISCOLORED, AND THERE WERE METAL SHAVINGS FOUND IN THE OIL.  (K)                                                                                                                                                                                                                                                                                         1H71 3O3  ONT3A13    E273                 
20060512000622006051200062CE  2006       5          12         2006FA0000426    120060412G2434E3FF10300AA     ALTERNATOR                              CESSNA210   T210M       2073451CE                                                               ENGINE          FAILED          B  WS9RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM07                                                                    ALTERNATOR FAILED, PLATE SCREWS FELL OUT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H71 3O      3A21                         
20060512001442006051200144WP  2006       5          12         2006FA0000427    120060412G62205143711         HUB                                     HILLERUH12  UH12E       4360122WP  LYC   O540  VO540C2A    41532EA                              MAIN ROTOR HUB  CRACKED         B  ECGRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA1346MV 2391 264               5046        L248043                     M/R HUB DYE CHECK INSPECTION.  HUB WAS FOUND TO BE CRACKED.  RETIREMENT LIFE, 2500 HOURS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1G71 3O3  O  4H11    E304                 
20060510001342006051000134EU  2006       5          10         2006FA0000428    120060421G3233273T411B1       ACTUATOR                                ROLSCHLS    LS3A        3801214EU  GE    CF6   CF680       30025NE                              NLG             CRACKED         B  DM4RK   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      SO19325OP                       3350                                    NLG RETRACT ACTUATOR WAS RECEIVED WITH THE PISTON ROD CRACKED.  3 CRACKS RUN AROUND THE CIRCUMFERENCE OF THE ROD AT THE THREADED END.  CRACKS RUN ABOUT 95 PERCENT AROUND ROD BUT DO NOT CONNECT (RUN IN A SPIRAL) CORROSION FOUND ON INTERIOR THREADS.  CORROSION APPEARS TO BE IN CRACK.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                 1K00   4  F  G37EU   E13NE                
20060511002892006051100289CE  2006       5          11         2006FA0000429    120060407G2750S19062          SWITCH                                  CESSNA172   172N        2072434CE                                                               FLAPS           STUCK           B  BNZRK   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      GL194668G                       17273294                                FLAP UP LIMIT SWITCH STUCK IN THE OPEN POSITION.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1H71 3O    NT3A12                         
20060512001522006051200152CE  2006       5          12         2006FA0000430    120060331G712034415377        MOUNT                                   BEECH 35    D35         1151510CE  CONT  E225  E2258       17015SO                              ENGINE          CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL212950B4649                   D3591       35004D286                   MOUNT WAS CROOKED IN WELD.  THINK IT HAPPENED DUE TO TIME ON PORT AND AGE OF AIRCRAFT.  CLOSE INSPECTION OF THIS AREA DURING ROUTINE MAINTENANCE (UPPER LT, MOUNT CLUSTER/ WEB .1250 INCH CRACK).  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L71 3O3  O  A777    E267                 
20060508000932006050800093SO  2006       5          8          2006FA0000431    120060418G3260211C24312       PRESSURE SWITCH                         PIPER PA28  PA28R200    7102811SO  LYC   O360  IO360C1C    41514EA                              LANDING GEAR    CORRODED        G      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      SW114967T                       28R7235164  RL1770951A                  LANDING GEAR FAILED TO RETRACT IN FLIGHT.  PLACING THE AC ON JACKS, THE LANDING GEAR FAILED TO COMPLETELY RETRACT.  BY PLACING A JUMPER WIRE BYPASSING THE HYDRAULIC PRESSURE SWITCH THE LANDING GEAR WORKED NORMALLY.  AFTER REMOVING THE PRESSURE SWITCH, CORROSION AND PITTING WAS OBSERVED ON THE CONTACTOR ALLOWING IT TO HEAT, WHICH INCREASED RESISTANCE, IN TURN CAUSING A LOW VOLTAGE CONDITION THAT DID NOT ALLOW THE GEAR MOTOR TO OPERATE AND CAUSED PARTIAL RETRACTION.  IT WAS NOTED THAT AS THE PRESSURE SWITCH COOLED, IT AGAIN ACTIVATED THE GEAR MOTOR AND CONTINUED THIS CYCLE UNTIL THE LANDING GEAR WAS IN THE UP POSITION.  (K)                                                                                           1L71 3O3  O  2A13    1E10                 
20060512001392006051200139SO  2006       5          12         2006FA0000432    120060418G571262021005        RIB                                     PIPER PA28  PA28R201    7102816SO                                                               WING STA 49.25  CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      NM13518MW1301                   2844105                                 RIB CRACKED IN FLANGE WHERE LANDING GEAR SIDE BRACE FITTING BOLTS.  THE CRACK HAS BEEN NOTED ON LIKE MODELS (6 WINGS).  ALL PREVIOUS NOTATIONS FOUND ON AC IN EXCESS OF 6000 HRS TO BE CAUSED BY AN IMPRESSION LEFT BY THE AN960-4 WASHER USED UNDER THE LOCKNUT.  THE WASHER APPEARS TO CUT INTO THE RADIUS AND THE CRACKS ORIGINATE AND FOLLOW THE WASHER OUTLINE UNTIL IT PROGRESSES TO A POINT OF CONTINUING IN BOTH DIRECTIONS VERTICALLY.  (K)                                                                                                                                                                                                                                                                                            1L71 3O      2A13                         
20060510002012006051000201SO  2006       5          10         2006FA0000433    120060414G571278475005        RIB                                     PIPER PA28  PA28R201    7102816SO                                                               RT WING STA49.25CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM13518MW1301                   2844105                                 INSPECTED RIB IAW SB 1161 AND FOUND RIB CRACKED.  THE SAME RIB HAS BEEN FOUND CRACKED IN THE SAME LOCATION ON SIX OTHER WINGS.  ALL OTHER WINGS HAD EXCESS OF 6000 HRS REPAIRED AND APPEARED TO HAVE BEEN INSTALLED CROOKED. THE ASSEMBLY PROCESS HAD THIS PART INSTALLED UNDER AN INITIAL LOAD LEADING TO PART CRACKING PREMATURELY.  (K)                                                                                                                                                                                                                                                                                                                                                                                                      1L71 3O      2A13                         
20060510002022006051000202EA  2006       5          10         2006FA0000434    220060414G8520                CAM                                     PIPER PA44  PA44180     7104402SO  LYC   O360  O360E1A6    41514EA                              ENGINE          WORN            D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM13336PA1100                   4496140                                 NOTED EXCESS MATERIAL IN REMOVED OIL FILTER, SAMPLE ANALYZED AND DETERMINED CAM/LIFTER WEAR.  ENGINE REMOVED FOR REPAIRS.  WHILE CASE SPLIT SB 569 COMPLIED WITH REPLACING CRANKSHAFT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L72 3O3  O  A19S0   E286                 
20060510002322006051000232EU  2006       5          10         2006FA0000435    120060411G6220109011211101    ROD END                                 AGUSTAA109  A119        0261102EU  PWA   PT6   PT6*        52043EA                              MAIN ROTOR      SEPARATED       D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP07820NA           0109        14011       PU0025                      DURING DAILY INSPECTION FOUND RED BLADE MAIN ROTOR DAMPER OB ROD END HAD COME APART.  BEARING HAD SEPARATED COMPLETELY FROM ROD END. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1G72 3U3  T  H7EU    E2NE                 
20060510002332006051000233EU  2006       5          10         2006FA0000436    120060405G29134005303         PUMP                                    AMD   FALC10FALCON10    2730101EU  GARRTTTFE731TFE731*     01518WP                              LT ENGINE       FAILED          B  BONRO   OTHER                                                                                           O  OTHER                                                                         TOTAKEOFF        1                      GL19700FH     1447              158                                     NR 1 HYDRAULIC PUMP FAILED ON TAKEOFF ROLL.  REMOVED PUMP AND INSPECTED BUT FOUND NO OBVIOUS PHYSICAL DEFECTS.  REMOVED HYDRAULIC SYSTEM FILTER AND INSPECTED FOR DEBRIS, NONE NOTED.  INSTALLED SERVICEABLE HYDRAULIC PUMP IN NR 1 POSITION, ALL SYSTEMS FUNCTION NORMALLY.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F4  F  A33EU   E6WE                 
20060510002182006051000218SO  2006       5          10         2006FA0000437    120060413G57126701603         RIB                                     PIPER PA28  PA28R180    7102809SO  LYC   O360  IO360A1A    41514EA                              WING            CRACKED         B  RMMRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE017536J2294                   28R30910                                DURING MODIFICATION OF AFT RIB IAW SB, 2 CRACKS WERE FOUND PROPAGATING FROM THE OB BOLT HOLE FOR THE ATTACHMENT OF (PN 9564307) BRACKET.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1L71 3O3  O  2A13    1E10                 
20060516001362006051600136    2006       5          16         2006FA0000438    120060417G2560BK05SL          PIN                                                                                                                                     SEAT BELT BUCKLEFAILED          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW05                                                                    DURING DYNAMIC CERTIFICATION TESTING,  2-PLACE SIDE FACING DIVAN, THE BUCKLE ON THE AFT ANTHROPOMORPHIC TEST DUMMY (ATD) POSITION RESTRAINT SYSTEM DISENGAGED ALLOWING THE ATD TO MOVE UNRESTRAINED.  PROBABLE CAUSE APPEARS TO BE FAILURE OF THE BUCKLE`S LOCKING PIN TO FULLY ENGAGE THE STRIKING PLATE (CONNECTOR) ON THE OPPOSITE HALF OF THE LAP BELT.  PART MAY HAVE BEEN DEFECTIVE.  MFG SHOULD IMPROVE INSPECTION PROCESS TO ENSURE THAT NO DEFECTIVE PARTS LEAVE THEIR FACILITY.  (K)                                                                                                                                                                                                                                                                                            
20060512001402006051200140EA  2006       5          12         2006FA0000439    220060128G853073938           INTAKE VALVE                            PIPER PA32  PA32300     7103212SO  LYC   O540  IO540*      41532EA                              CYLINDER NR 3   DISINTEGRATED   B  XXORK   NONE                                                                                            ER VIBRATION/BUFFET          PARTIAL RPM/PWR LOSS                                NRNOT REPORTED   1                      WP0156709127                    327440020                               INTAKE VALVE DISINTEGRATED, FALLING INTO CYLINDER HEAD NR 3.  VALVE BOUNCED AROUND, BEATING THE TOP OF PISTON AND CYL HEAD CAUSING EXTENSIVE DAMAGE, FINALLY THE VALVE WAS SUCKED INTO THE INTAKE CAUSING A GAPPING HOLE ON THE INTAKE PORT.  INTAKE VALVE FAILURE IS BELIEVED TO BE THE ONLY CAUSE OF CATASTROPIC FAILURE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                1L71 3O3  O  A3SO    1E4                  
20060508000522006050800052    2006       5          8          2006FA0000440    420060223G34178220839429      ADC                                     LEAR  60    60LEAR      5170707CE  PWA   305   PW305            NE                              LT AFT AVIONICS DEFECTIVE       B  BSYRO   OTHER                                                                                           S  AFFECT SYSTEMS                                                                CRCRUISE         1                      GL07160AN                       126                                     ALL ADC OUTPUTS ON THE COPILOTS PFD (ALTIMETER, VSI AND AIRSPEED, ECT) FLAGGED IN FLIGHT INTERMITTENTLY AND WOULD RESET ITSELF.  CREW REQUESTED TO LEAVE RVSM AIRSPACE.  THE ADC WAS FOUND TO BE DEFECTIVE AND WAS REPLACED.  THE SYSTEM WAS TESTED AND INSPECTED IAW MM AND FOUND TO COMPLY WITH FAR 91.411 PART 43 AND MFG RVSM ADC INSPECTIONS.  THE AIRCRAFT REMAINS RVSM COMPLIANT.  (K)                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  FRTA10CE   E35NE                
20060511002732006051100273SO  2006       5          11         2006FA0000441    220060417G8550CH48110         OIL FILTER                              CESSNA182   182P        2075816CE  CONT  O470  O470*       17026SO                              ENGINE          MISMANUFACTURED D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO1358946                       18262417                                MOUNTING STUD TOO LONG, APPROX .200 LONGER.  INSTALLED OIL FILTER AFTER OIL CHANGE, RAN ENGINE TO LEAK CHECK AND LOST ALMOST 2 QTS OF OIL.  INVESTIGATION FOUND THAT THE OIL FILTER STUD WAS TOO LONG CAUSING THE FILTER TO TORQUE BEFORE SEAL TOUCHED FLANGE, LEAVING .050 GAP.  REPLACED FILTER WITH SAME PN BUT WITH SHORTER STUD AND LEAK CHECKED, OK.  (K)                                                                                                                                                                                                                                                                                                                                                                                 1H71 3O3  ONTTA13    E273                 
20060512001582006051200158SO  2006       5          12         2006FA0000442    120060323G2910                HYDRAULIC LINE                          PIPER PA23  PA23250     7102308SO  LYC   O540  IO540*      41532EA                              RT CABIN SIDE   CHAFED          D      O   OTHER                                                                                           K  FLUID LOSS                                                                    APAPPROACH       1                      EA07638688803                   277854020                               COMPLETE INTERIOR REFURBISHING WAS DONE.  100 HRS AFTER AC WAS RETURNED TO SERV, NOSE AND LT MAIN GEAR WOULD NOT LOCK DOWN, PILOT LANDED WITH ONLY RT GEAR EXTENDED.  HYD FLUID WAS DRIPPING FROM BELLY,  UPON INVESTIGATION, ALUMINUM HYD LINE WAS CHAFED THROUGH BY AILERON CABLE IN FRONT OF MAIN SPAR, UNDER CABIN ENTRANCE DOOR SILL.  SUSPECTED THAT AFTER AC WAS INSP, WHEN DISCREP WERE BEING CLEARED, INTERIOR WORK BEING DONE, PERSONNEL SOMEHOW BENT LINE DOWN TO WHERE IT CONTACTED CABLE.  WHEN PANEL IS REMOVED UNDER DOOR, HYD LINES ARE EXPOSED, LITTLE SUPPT IN THIS AREA, LITTLE CLEARANCE BTWN LINES, CABLES.  LINES, CABLES ON LT SIDE OF CABIN ARE LESS LIKELY TO BE DISTURBED AS AUTOPILOT ROLL SERVO PROTECTS THEM.  (K) 1L72 3O3  O  1A10    1E4                  
20060512001432006051200143NM  2006       5          12         2006FA0000443    120060419G5400F2MA581200817   COWLING                                 AMD   FALC50FALCON2000  2730170NM                                                               LT ENGINE       SEPARATED       B  UO2RA   UNSCHED LANDING                                                                                 D  INFLIGHT SEPARATION                                                           CRCRUISE         1                      GL19722JB                       13                                      AIRCRAFT WAS RETURNING TO HOME FIELD AFTER MAINTENANCE WHEN CREW HEARD A LOUD NOISE AND ELECTED TO RETURN TO DEPARTURE.  AFTER ENGINE SHUTDOWN, IT WAS DETERMINED THAT THE LT ENGINE UPPER AND LOWER COWLING HAD SEPARATED FROM THE AC IN FLIGHT.  SB CONCERNING COWLING SEPARATION, HAD BEEN PREVIOUSLY APPLIED.  COWL SEPARATION HAS BEEN THE SUBJECT OF PREVIOUS SERVICE ADVISORIES AND SERVICE NEWS FLASHES.  (K)                                                                                                                                                                                                                                                                                                                           2K72 4F    RTA50NM                        
20060511002852006051100285NM  2006       5          11         2006FA0000444    120060419G5400F2MA581260813   COWLING                                 AMD   FALC50FALCON2000  2730170NM                                                               LT ENGINE       SEPARATED       B  UO2RA   UNSCHED LANDING                                                                                 D  INFLIGHT SEPARATION                                                           CRCRUISE         1                      GL19722JB                       13                                      AC WAS RETURNING TO HOME FIELD AFTER MAINTENANCE WHEN CREW HEARD A LOUD NOISE AND ELECTED TO RETURN TO DEPARTURE.  AFTER ENGINE SHUT-DOWN, IT WAS DETERMINED THAT THE LT ENGINE UPPER AND LOWER COWLING HAD SEPARATED FROM THE AC IN FLIGHT.  SB CONCERNING COWLING SEPARATION, HAD BEEN PREVIOUSLY APPLIED.  COWL SEPARATION HAS BEEN THE SUBJECT OF PREVIOUS SERVICE AD AND SERVICE NEWS FLASHES.  (K)                                                                                                                                                                                                                                                                                                                                        2K72 4F    RTA50NM                        
20060508001652006050800165CE  2006       5          8          2006FA0000445    120060330G5610NH2401691       WINDSHIELD                              RAYTHNDH125 HAWKER800XP 7150012CE  GARRTTTFE731TFE731*     01518WP                              COCKPIT         CRACKED         D      BA  EMER. DESCENT           UNSCHED LANDING                                                         O  OTHER                                                                         CRCRUISE         1                      EA07333PC4619                   258277                                  LEVEL FLIGHT AT 360, PILOTS (B) PANEL OUTER HEATED LAYER CRACKED ALONG LOWER FRONT CORNER THEN CONTINUED UP AND ACROSS TOP OF WINDOW.  CREW DECLARED AN EMERGENCY AND DESCENDED TO 8000 FT.  OUTER PANEL STAYED WITH AIRCRAFT, NO AD OR SB APPLY TO PANEL AT THIS TIME.  WINDOW REPLACED WITH NEW UNIT.  PRESSURIZATION AND OPS CHECK GOOD.  THIS WINDOW HAD NO VISIBLE OR OPERATIONAL PROBLEMS PRIOR TO FAILURE.  (K)                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA3EU    E6WE                 
20070511001532007051100153SW  2007       5          11         2006FA0000446    120060410G62103G6220A00251    BOLT                                    AGUSTAAB139 AB139       0260110SW  PWA   PT6   PT6*        52043EA                              MAIN ROTOR      GOUGED          B  LWXRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW19139HS50                     31016                                   DURING ACCOMPLISHMENT OF THE MAIN ROTOR BLADE REMOVAL, IT WAS DISCOVERED THAT EACH OF THE BLADE BOLTS HAS RADIAL GOUGE MARKS AT THE BLADE TO HUB BUSHING LOCATIONS.  THE DAMAGE IS OUTSIDE THE AMM PERMITTED REPAIR LIMITS.  (REFERENCE: 39A62221300A286AB) MFG HAS BEEN CONTACTED AND PROVIDED THIS INFORMATION.  (NOTE:  THERE ARE ALSO TYPOGRAPHICAL ERRORS IN THE AMM MILLIMETER TO INCHES CONVERSIONS IN FIGURE 2 INCH (MAXIMUM DAMAGE AND REPAIR DEPTHS).  FIG CALLS OUT (MM/IN) 0.02 / 0.0080, SHOULD BE  0.0008.  (K)                                                                                                                                                                                                                   2G72 6U3  T  R00002RDE2NE                 
20060509001992006050900199SO  2006       5          9          2006FA0000447    120060226G32131180500         STRUT                                   PIPER PA17  PA17        7101702SO  CONT  A65   A65*        17003SO                              LANDING GEAR    CORRODED        D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL134879H725                    17178                                   CHANGING SHOCK CORDS, DISCOLORATION OF INNER STRUT TUBE (LONGER ONE), REMOVED IT FROM OUTER TUBE (SHORTER ONE) OF INNER STRUT TUBES WAS CORRODED APPROX 50 PERCENT OF CIRCUM.  OTHER INNER STRUT HAD MULTIPLE CORROSION HOLES THROUGH METAL.  BOTH SHORT TUBES (OUTER) SHOWED  ELONGATION AT ENDS INDICATING FLEXING/ BENDING OF ASSY DURING LANDING/TAKEOFF.  ONLY NEW BUNGEES KEPT GEAR FROM FINAL FAILURE,  RESULTANT GROUND LOOP.  BUNGEE CORDS, WHEN INSTALLED, COVER THIS AREA, USUALLY HAVE A CLOTH OR ALUMINUM FAIRING OVER THEM.  DETECTION REQUIRES REMOVAL OF FAIRINGS AT A MINIMUM, AND REMOVAL OF BUNGEES TO CLEARLY SEE OUTER TUBES CIRCUM.  NECESSARY TO DISASSEMBLE UNIT, VIEW INNER PIECE, OUTER PIECE SEPARATELY.   (K)       1H71 3O3  O  A805    E205                 
20060509002372006050900237SO  2006       5          9          2006FA0000448    220060414G73226297032         FCU                                     CESSNA210   210E        2073416CE  CONT  O520  IO520A      17032SO                              ENGINE          WORN            D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA03     2240                               1740067F                    FOUND SHAFT AND LINKAGE EXCESSIVELY WORN.  HAD COMPLETE ASSEMBLY OVERHAULED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1H71 3O3  O  3A21    E5CE                 
20060510001302006051000130CE  2006       5          10         2006FA0000449    120060501G33206900042000      LIGHT           BEECH                   BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA                              CABIN           BURNED OUT      C      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      ININSP/MAINT     1                      SO11800HA                       BB220                                   FLUORESCENT LIGHT ASSY FAILED AND DISPERSED SMOKE IN CABIN. POWER SUPPLY GOT HOT AND DAMAGED ADJACENT INSULATION. LIGHT ASSY WAS REPLACED WITH FACTORY NEW.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L72 4T4  T  A24CE   E4EA                 
20060510001332006051000133CE  2006       5          10         2006FA0000450    120060501G33206900042000      LIGHT           BEECH                   BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA                              CABIN           BURNED OUT      C      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      ININSP/MAINT     1                      SO11800HA                       BB220                                   FLUORESCENT LIGHT ASSY FAILED AND DISPERSED SMOKE IN CABIN. POWER SUPPLY GOT HOT AND DAMAGED ADJACENT INSULATION. LIGHT ASSY WAS REPLACED WITH FACTORY NEW.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L72 4T4  T  A24CE   E4EA                 
20060509002412006050900241EA  2006       5          9          2006FA0000451    220060505G8530                VALVE           LYC         0360J2A                                        LYC   O360  O360J2A     41514EA                                              MALFUNCTIONED   P  JWEGR   AUTOROTATION                                                                                    E  VIBRATION/BUFFET                                                              CRCRUISE         1                      SW09                L3963136A               L3963136A                   NEW ENGINE IN NEW HELICOPTER. AFTER FLYING 1.5 HOURS, ENGINE WILL START POPPING AND BACKFIRING, CAUSING AN AUTOROTATION.  MFG SAID IT'S A NORMAL MAINTENANCE ITEM TO REMOVE VALES AND REAM VALVE GUIDES.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               3  O          E286                 
20060512000502006051200050EA  2006       5          12         2006FA0000452    220060425G7322MA4SPA105135    CARBURETOR                              PIPER PA28  PA28161     7102803SO  LYC   O320  O320D3G     41508EA                              ENGINE          UNSERVICEABLE   D      O   OTHER                                                                                           YK ENGINE STOPPAGE           FLUID LOSS                                          TXTAXI/GRND HDL  1                      EA172203T     800               287916300                               REF:  NM-02-47 DATED 9/30/02 AND CE-06-33R1, DATED 4/12/06.  ENGINE QUITS AT IDLE; IDLE SET AT 600, WILL DROP OFF AND QUIT.  FUEL SOMETIMES DRAINS FROM CARB AFTER SHUTDOWN.  BOTH SYMPTONS MATCH THOSE IN NM-02-47.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L71 3O3  O  2A13    E274                 
20060510002382006051000238SO  2006       5          10         2006FA0000453    220060418G8530AEC65385        CYLINDER                                BEECH 58    58          1152740CE  CONT  O550  IO550C           SO                              RT ENGINE       CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW013149P1301 1301              TH1470      810387R                     NR 1 CYLINDER CRACKED AT SPARK PLUG HOLE.  (RT ENGINE) (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L72 3O3  O  3A16    E3SO                 
20060510002392006051000239SO  2006       5          10         2006FA0000454    220060418G8530AEC65385        CYLINDER                                BEECH 58    58          1152740CE  CONT  O550  IO550*           SO                              LT ENGINE       CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW013149P1301 1301              TH1470      810386R                     NR 5 CYLINDER CRACKED AFT OF VALVES.  (STILL HAD GOOD COMPRESSION BUT COULD HEAR AIR) (LT ENGINE) (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L72 3O3  O  3A16    E3SO                 
20060512000512006051200051SO  2006       5          12         2006FA0000455    220060418G8530AEC65385        CYLINDER                                BEECH 58    58          1152740CE  CONT  O550  IO550*           SO                              LT ENGINE       CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW013149P1301 1301              TH1470      810386R                     NR 2 CYLINDER COMPLETELY CRACKED ALL THE WAY AROUND AFT OF VALVES.  (LT ENGINE) (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L72 3O3  O  3A16    E3SO                 
20060510002412006051000241SO  2006       5          10         2006FA0000456    220060418G8530AEC65385        CYLINDER                                BEECH 58    58          1152740CE  CONT  O550  IO550*           SO                              LT ENGINE       CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW013149P1301 1301              TH1470      810386R                     NR 6 CYLINDER CRACKED AFT OF VALVES.  (STILL HAD GOOD COMPRESSION COULD HEAR AIR.) (LT ENGINE) (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L72 3O3  O  3A16    E3SO                 
20060512000582006051200058SO  2006       5          12         2006FA0000457    220060418G8530AEC65385        CYLINDER                                BEECH 58    58          1152740CE  CONT  O550  IO550*           SO                              LT ENGINE       CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW013149P1301 1301              TH1470      810386R                     NR 4 CYLINDER CRACKED AFT OF VALVES.  (STILL HAD GOOD COMPRESSION BUT COULD HEAR AIR) (LT ENGINE) (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L72 3O3  O  3A16    E3SO                 
20060512000592006051200059CE  2006       5          12         2006FA0000458    120060419G27500400107146      CABLE                                   CESSNA150   152         2071835CE  LYC   O235  O235*       41505EA                              FLAP CONT SYS   BROKEN          D      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             APAPPROACH       1                      NM095494P12872                  15284959                                ON FINAL, STUDENT SELECTED 30 DEGREE FLAPS, A LOUD POP WAS HEARD, RT FLAP CAME DOWN TO 30 DEGREES, NO MOVEMENT AT LT FLAP. AIRCRAFT LANDED WITHOUT INCIDENT.  INVESTIGATION REVEALED SWAGGED BALL END OF CABLE, PN 0400107-146 BROKE FROM REMAINING CABLE.  SUSPECT HIGH TIME AND CYCLES AS CONTRIBUTING FACTORS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3O3  ONT3A19    E223                 
20060512000452006051200045SO  2006       5          12         2006FA0000459    120060419G5341                ATTACH FITTING                          PIPER PA25  PA25235     7102504SO  LYC   O540  O540*       41532EA                              FUSELAGE        OUT OF LIMITS   D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL216719Z3732                   252328                                  ATTACHMENT CONNECTIONS AT RT AND LT SIDES ARE BELOW MINIMUM SPECIFIED IN AD.  INSPECTION METHOD- ULTRASONIC.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L71 3O3  O  2A10    E295                 
20060517002362006051700236CE  2006       5          17         2006FA0000460    120060413G2840S38521          GAUGE                                   CESSNA172   172R        2072401CE  LYC   IO360 IO360L2A         EA                              LT FUEL TANK    FLUCTUATES      B  BNZRK   NONE                                                                                            N  FALSE WARNING                                                                 NRNOT REPORTED   1                      GL195335G50                     17281158                                PART HAS A DEAD SPOT IN ITS TRAVEL CAUSING FUEL GAUGE TO FLUCTUATE RAPIDLY BETWEEN FULL AND EMPTY ALSO CAUSES LOW FUEL WARNING LIGHT TO FLASH CONTINUOUSLY.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1H71 3O3  ONT3A12    1E10                 
20060511001822006051100182CE  2006       5          11         2006FA0000461    120060314G2842S38522          SENSOR                                  CESSNA172   172R        2072401CE  LYC   IO360 IO360L2A         EA                              RT FUEL TANK    FLUCTUATES      B  BNZRK   NONE                                                                                            N  FALSE WARNING                                                                 NRNOT REPORTED   1                      GL195335G86                     17281158                                PART HAS A DEAD SPOT IN ITS TRAVEL (NEAR FULL POSITION AT TOP OF TRAVEL) CAUSING FUEL GAUGE TO FLUCTUATE RAPIDLY BETWEEN FULL AND EMPTY, ALSO CAUSES LOW FUEL WARNING LIGHT TO FLASH CONTINUOUSLY.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1H71 3O3  ONT3A12    1E10                 
20060511001842006051100184    2006       5          11         2006FA0000462    420060316G611305503214        BULKHEAD                                CESSNA172   172N        2072434CE  LYC   O320  O320D2G     41508EA                              SPINNER         CRACKED         C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM01734QQ292                    17269034    L3871627A                   DURING ROUTINE PHASE INSPECTION FWD PROP BULKHEAD FOUND TO BE CRACKED NEAR SEVERAL MOUNTING BOLT HOLES.  HAVE SEEN THIS SEVERAL TIMES BEFORE.  SUSPECT DEFECT IN CURRENT MFG PROCESS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1H71 3O3  ONT3A12    E274                 
20060512000752006051200075CE  2006       5          12         2006FA0000463    120060427G3246300257          WHEEL                                   BEECH 90    C90A        1152911CE                                                               MLG             CRACKED         C      K   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      NM01164WS199        A5643       LJ1736                                  CRACKED IB WHEEL HALF CAUSING LOSS OF TIRE AIR PRESSURE.  NOTE:  THIS WAS A BRAND NEW PART ON A NEW AIRPLANE.  NOT AN OVERHAULED PART (SEE 5(I) AND 6(I)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L72 3T    RT3A20                         
20060512001332006051200133CE  2006       5          12         2006FA0000464    120060509G5741130909B103      BOLT                                    BEECH 36    B36TC       1151609CE                                                               WING ATTACH     CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL117258E142                    EA455                                   MAG PART INSP FOUND FWD WING ATTACH POINTS BOLT P/N 130909B103 AND 131790-3 WITH CRACKS.  THE BOLTS WERE INSTALLED NEW IN FWD WING BOLT FITTINGS ON BEECH MODEL 36 SERIES AIRCRAFT S/N EA-455 ON 1/25/2002. THE LH UPPER BOLT (P/N 130909B103) WAS REMOVED FOR IT'S FIRST 5 YEAR NDT INSPECTION AND WAS CRACKED AT THE HEAD RADIUS USING MAG PART NDT PROCESS. PART TOTAL TIME 142 HRS SINCE INSTALLED. NO DAMAGE NOTED ON THE ASSOCIATED WING FITTING THAT WOULD INDICATE A CONTRIBUTING STRESS CONDITION. THE RT LOWER WING BOLT ON THE OPPOSITE SIDE OF THE A/C WAS ALSO CRACKED IN THE SAME LOCATION. THIS BOLT IS A DIFFERENT P/N (131790-3). BEECH TECH SUPPORT WAS GIVEN THE BOLTS & INFO FOR EVALUATION.                                1L71 3O      3A15                         
20060512001342006051200134CE  2006       5          12         2006FA0000465    120060509G57411317903         BOLT                                    BEECH 36    B36TC       1151609CE                                                               WING ATTACH     CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL117258E142                    EA455                                   MAG PART INSP FOUND FWD WING ATTACH POINTS BOLT P/N 130909B103 AND 131790-3 CRACKED.  BOLTS INSTALLED NEW IN FWD WING BOLT FITTINGS ON BEECH MODEL 36 SER A/C S/N EA-455 ON 1/25/2002. THE LT UPPER BOLT (P/N 130909B103) REMOVED FOR FIRST 5 YEAR NDT INSPECTION AND WAS CRACKED AT THE HEAD RADIUS. USED MAG PART INSP. TTSN 142 HRS. NO DAMAGE WAS NOTED ON THE ASSOCIATED WING FITTING THAT WOULD INDICATE A CONTRIBUTING STRESS CONDITION. RT LOWER WING BOLT ON THE OPPOSITE SIDE OF THE A/C ALSO CRACKED IN SAME LOCATION. THIS BOLT IS A DIFFERENT P/N (131790-3). BEECH TECH SUPPORT GIVEN BOLTS AND ALL THE INFO PERTINENT TO THESE PARTICULAR BOLTS FOR EVALUATION. OPERATING CONDITIONS OF THE AIRCRAFT ARE UNKNOWN.                1L71 3O      3A15                         
20060511001872006051100187EA  2006       5          11         2006FA0000466    220060410G8520                CONNECTING ROD                          GULSTM500   500S        0141107SW  LYC   O540  IO540E1B5   41532EA                              RT ENGINE       BROKEN          B  BOERO   OTHER                                                                                           Y  ENGINE STOPPAGE                                                               CRCRUISE         1                      GL1990JP                        3078        L805848                     CUSTOMER WAS ENROUTE TO MAINTENANCE SHOP TO GET ANNUAL INSPECTION, BOTH ENGINES OVERHAULED.  RT ENGINE CYLINDER NR 2 CONNECTING ROD BROKE AT THE CRANKSHAFT ATTACHMENT CAUSING MAJOR DAMAGE TO THE CAMSHAFT, AND CRANKCASE BREAKING OPEN IN SEVERAL PLACES AROUND THE FRONT PART OF THE ENGINES.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                           1H72 3O3  O  6A1     1E4                  
20060517002372006051700237SO  2006       5          17         2006FA0000467    220060410G8530631397          CYLINDER                                CESSNA340   340A        2076405CE  CONT  O520  TSIO520NB   17040SO                              ENGINE          CRACKED         C  BOERK   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      GL19984MW                       340A0070    521294                      AT 400 HR TSO FOUND CYLINDER NR 4 CRACKED AT THE HEAD 5 FINS BACK TOWARD THE BARREL FROM THE TOP SPARK PLUG.  CRACK GOES FROM THE EXHAUST VALVE SEAT TO THE TOP SPARK PLUG HOLE ON THE INSIDE OF THE CYLINDER.  AD 04-08-10 DID NOT APPLY BY CLY.  SN 13516-4 AND CODE A STAMPED ON THE BOSS FLANGE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 3O3  O  3A25    E8CE                 
20060517002172006051700217    2006       5          17         2006FA0000468    420060419G3425NSD360          HSI                                     CESSNA340   340A        2076405CE  CONT  O520  TSIO520*    17040SO                              COCKPIT         DEACTIVATED     B  F3ORO   OTHER                                                                                           G  MULTIPLE FAILURE                                                              NRNOT REPORTED   1                      SO03594HS                       340A0440                                PILOT REPORTED HSI WAS INOPERATIVE AND SUSPECTED A PLUG WAS OFF.  VISUAL INSPECTION REVEALED THAT THE PUG TO THE HSI, AND THE VACUUM HOSE HAD BOTH BEEN PULLED OFF BY THE AC CONTROL WHEEL.  THE HOSES AND WIRING HARNESS HAD BEEN INCORRECTLY ROUTED AROUND THE CONTROL WHEEL.  THE AC HAD VERY LITTLE ROOM BEHIND THE INSTRUMENT PANEL, AND THE CORRECT ROUTING OF HOSES AND HARNESSES IS CRITICAL TO FLIGHT SAFETY.  THE CONTROLS WERE FREE AFTER THE HOSE AND HARNESS CAME OFF THE PILOTS HSI. WITH MORE AC BEING UPGRADED WITH NEWER AVIONICS AND INSTRUMENTS, INSPECTIONS OF HARNESSES AND HOSES BEHIND THE INSTRUMENT PANEL IS AN AREA THAT REQUIRES INCREASED VIGILANCE.  (K)                                                           1L72 3O3  O  3A25    E8CE                 
20060512001382006051200138CE  2006       5          12         2006FA0000469    120060426G81004656809004      TURBOCHARGER                            CESSNA210   P210N       2073454CE  CONT  O520  TSIO520P    17040SO                              ENGINE          LEAKING         B  WS9RK   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      NM074773P                       P21000102                               OIL LEAKING OUT FROM JOINT IN CENTER OF TURBO. FIRST RUN ON OVERHAULED UNIT JUST INSTALLED ON AIRCRAFT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H71 3O3  O  3A21    E8CE                 
20060807000962006080700096    2006       8          7          2006FA0000470    120060404G8011X13041          BEARING                                                                    CONT  O520  TSIO520C    17040SO                              STARTER         FAILED          B  R04RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM04     1                                                              WHILE REMOVING THE STARTER FOR MAINTENANCE, THE STARTER ADAPTER WORM SHAFT ROLLER BEARING RETAINER CAGE HALF WAS FOUND STUCK TO THE STARTER FLANGE.  ALL THE ROLLER BEARING BALLS WERE STILL IN THEIR RACES BUT BLUISH IN COLOR.  AFTER DISASSEMBLING THE ADAPTER, THE INNER HALF AND SMALLER PIECES OF THE CAGE WERE FOUND IN THE LOWER RECESSES OF THE  ADAPTER HOUSING. FORTUNATELY, NONE WAS SUSPECTED TO HAVE ENTERED THE ENGINE SUMP. IT WAS SUSPECTED THAT THE STARTER RELAY REMAINED ENGAGED AND THE STARTER WAS ENERGIZED DURING ONE OR MORE GROUND RUNS.                                                                                                                                                                                     3  O          E8CE                 
20060613002102006061300210CE  2006       6          13         2006FA0000471    120060412G3246300257          WHEEL HALF      BFGOODRICH              BEECH 90    C90A        1152911CE                                                               LT MLG          CRACKED         C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW99164WS177        A5665       LJ1736                                  LEFT MAIN WHEEL (INBOARD HALF) FOUND CRACKED.  PROBLEM SHOWED ITSELF DUE TO WHEEL/TIRE ASSY SUFFERING A SLOW LEAK OF AIR PRESSURE.  THIS IS NOT THE SAME PROBLEM REPORTED FOR THIS AIRCRAFT ON 4/27/2006.  THIS IS A PREVIOUS OCCURRENCE ON THE OTHER SIDE.  BOTH MAIN WHEELS HAVE NOW BEEN CHANGED.                                                                                                                                                                                                                                                                                                                                                                                                                                            1L72 3T    RT3A20                         
20060613002342006061300234CE  2006       6          13         2006FA0000472    120060502G284299144272        FLOAT SWITCH                            CESSNA560   560XL       2076702CE                                                               FUEL SYS        INOPERATIVE     B      K   NONE                                                                                            B  SMOKE/FUMES/ODORS/SPARKS                                                      NRNOT REPORTED   1                      GL09635QS2291                   5605358                                 THE RIGHT LOW FUEL LEVEL SYSTEM WAS INOPERATIVE.  REMOVED SWITCH AND FOUND SIGNS OF ARCING ON THE TOP SIDE OF THE SWITCH.  TROUBLESHOT FURTHER AND FOUND THE PC BOARD WAS DEFECTIVE.  IT IS NOT KNOWN IF THE SWITCH DAMAGED THE PC BOARD.  THIS IS NOT THE FIRST TIME WE HAVE SEEN A DEFECTIVE FLOAT SWITCH WITH SIGNS OF ARCING, HOWEVER, IT IS THE FIRST TIME THAT A DAMAGED PC BOARD WAS ASSOCIATED WITH IT.  IT WAS NOTED THAT WHEN THE FLOAT SWITCH IS IN THE 'HIGH FUEL LEVEL' POSITION THE CONTACT SURFACES ARE ALIGNED.  WHEN THE SWITCH IS IN THE 'LOW FUEL LEVEL' THE CONTACTS ARE NEARLY COMPLETELY MISALIGNED.                                                                                                                      2L72 4F    RTA22CE                        
20060511003012006051100301CE  2006       5          11         2006FA0000473    120060510G29102607003453      HYDRAULIC LINE                          LEAR  35    35A         5170602CE                                                               REAR EQUIP BAY  LEAKING         B      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      SO13222BG                       35A448                                  PRE-FLIGHT FOR SECOND LEG OF FLIGHT CREW REPORTED HYDRAULIC FLUID DRIPPING OUT OF REAR EQUIPMENT BAY. INSPECTION REVEALED THAT THE HYDRAULIC PRESSURE LINE HAD CHAFED THROUGH AND WAS LEAKING FLUID. INSTALLED NEW LINE. COMPLIED WITH PRESSURE CHECK OF SYSTEM WITH NO ADDITIONAL LEAKS NOTED. CHECKED ROUTING OF LINE AND INSTALLED CHAFE MATERIAL WHERE NEEDED. PART HOURS OR CYCLES UNKNOWN.                                                                                                                                                                                                                                                                                                                                                2L72 4F      A10CE                        
20060518002612006051800261EU  2006       5          18         2006FA0000474    120060510G3246AHA1814         WHEEL HALF                              BRAERODH125 BAE125800A  1500285EU                                                               LANDING GEAR    CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO132QG                         NA0467                                  DURING ROUTINE TIRE CHANGE AND EDDY CURRENT INSPECTION OF DUNLOP MAIN WHEEL HALF AND FLANGE. EDDY CURRENT INSPECTION REVEALED TWO CRACKS WHICH RADIATED OUT FROM WHEEL TIE BOLT HOLE. BOTH CRACKS WERE APPROMIXATELY .050 INCHES IN LENGTH. PART WAS REJECTED AND REPLACED WITH NEW PART. WHEEL PART NO. AHA1814 FLANGE PART NO.AH43949. PART HOURS OR CYCLES UNKNOWN.                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA3EU                         
20060518002622006051800262CE  2006       5          18         2006FA0000475    120060510G2730083200054       HINGE BRACKET   CESSNA                  CESSNA421   421B        2076014CE                                                               RT ELEVATOR     ELONGATED       B      K   NONE                                                                                            E  VIBRATION/BUFFET                                                              DEDESCENT        1                      WP231944G8307                   421B0844                                CUSTOMER REPORTED VIBRATION AT HIGH SPEEDS. INSPECTED AIRCRAFT AND FOUND CENTER ELEVATOR HINGE IB AND OB BRACKETS ELONGATED ON THE RT ELEVATOR.   INSTALLED MFG SERVICE KIT SK421-130B REPLACING ALUMINUM ELEVATOR HINGE BRACKETS WITH STAINLESS STEEL BRACKETS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L72 3O      A7CE                         
20060519002422006051900242WP  2006       5          19         2006FA0000476    220060426G72108687813         GEAR                                    MTSBSIMU2   MU2B36A     5780413CE  GARRTTTPE331TPE33110T        WP                              LT ENGINE GRBOX CRACKED         B  IZ2RO   OTHER                                                                                           EY VIBRATION/BUFFET          ENGINE STOPPAGE                                     CRCRUISE         1                      SW15777LP                       719SA                                   PILOT REPORTED DURING CRUISE LEVEL FLIGHT FEELING A SUDDEN VIBRATION AND HEARING A SCREAMING NOISE FROM THE LT ENGINE.  PILOT THEN NOTICED TORQUE INDICATION ON LT ENGINE INDICATING 120 PERCENT WITH NO YAW INDICATED OR NOTICED BY PILOT. WHILE RETARDING LT POWER LEVER TO REDUCE TORQUE THE LT ENGINE SHUTDOWN UNCOMMANDED.  ENGINE NTS SYSTEM FUNCTIONED NORMALLY AND AN UNEVENTFUL SINGLE ENGINE LANDING WAS MADE.  UPON ENGINE ASSEMBLY A 2 INCH PIECE OF THE BULL GEAR OUTER RIM WAS LAYING IN THE BOTTOM OF THE ACCESSORY HOUSING.  INSPECTION OF THE BULL GEAR REVEALED THE MISSING SECTION AND AN APPROX 4 INCH CRACK IN THE HUB AREA WHICH CAUSED LOSS OF DRIVE TO THE PROPELLER SHAFT.                                             1H72 3T4  T  A10SW   E4WE                 
20060517002082006051700208EA  2006       5          17         2006FA0000478    220060501G7414S6LSC21BL5005162MAGNETO                                 PIPER PA25  PA25235     7102504SO  LYC   O540  O540B2C5    41532EA                              ENGINE          DISINTEGRATED   D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO167339Z     740               253289      L1154840                    MAGNETO WAS REMOVED FROM ENGINE FOR ROUTINE MAINTENANCE INSPECTION.  THREADS ON MAGNETO SHAFT AND NUT WERE COMPLETELY STRIPPED.  SLOT IN SHAFT FOR WOODRUFF KEY WAS WALLOWED OUT.  COTTER KEY WHICH RETAINED NUT TO SHAFT WAS STILL IN PLACE. AT TIME OF REMOVAL ENGINE WAS OPERATING NORMALLY.  ONLY THE MAG BUSHINGS AND RETAINER WERE HOLDING THE IMPULSE COUPLING IN PLACE.  THE DRIVE SHAFT AND OR THE WOODRUFF WERE DEFECTIVE AT THE TIME OF MANUFACTURE.  THIS CONDITION IF UNDETECTED WILL LEAD TO COMPLETE ENGINE FAILURE.  (K)                                                                                                                                                                                                        1L71 3O3  O  2A10    E295                 
20060518001322006051800132CE  2006       5          18         2006FA0000479    120060508G240070008840        CIRCUIT BREAKER                         LEAR  35    35A         5170602CE  GARRTTTFE731TFE731*     01518WP                              COCKPIT         TRIPPED         C      B   EMER. DESCENT                                                                                   HG ELECT. POWER LOSS-50 PC   MULTIPLE FAILURE                                    CRCRUISE         1                      SW11242MT10053                  621                                     (ELECTRICAL ANOMALY), LT AND RT ESSENTIAL (A) CIRCUIT BREAKERS DEPLOYED.  ALL EFIS WENT DARK.  YAW DAMP AND AUTO PILOT DISENGAGED.  LOST ALL NAV AND COMM. RADIOS, LOST ANNUNCIATOR PANEL LIGHTS.  MAY HAVE LOST AIRSPEED INDICATORS AND FUEL COMPUTERS.  LOST BOTH N 1S .  BOTH ITTS, DC AND AC ELECTRICAL INDICATORS FUNCTIONED NORMALLY AND INDICATED NORMAL ELECTRICAL SYSTEM CONDITION.  GEAR, FLAPS, SPOILERS, TRIMS, TRS ALL FUNCTIONED NORMALLY.  TR ARM AND DEPLOY LIGHTS DID NOT WORK.                                                                                                                                                                                                                                             2L72 4F4  F  A10CE   E6WE                 
20060516001832006051600183    2006       5          16         2006FA0000480    420060503G2215                ROLL SERVO                              GULSTM112   112A        7630302SW  LYC   O360  IO360A1A    41514EA                              AUTO PILOT SYS  MISINSTALLED    B  TP4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO151346J                       346                                     THE ROLL SERVO WAS INSTALLED AND RIGGED INCORRECTLY, THE SET WAS NOT TIGHT ON THE BRIDLE CABLE PIN AND THE BRIDLE CABLE WAS WRAPPED ON THE CAPSTAN INCORRECTLY.  THE INCORRECT INSTALLATION IN CONJUNCTION WITH THE LOOSE SET SCREW ALLOWED THE BRIDLE CABLE LOCATING PIN TO PULL OUT OF THE SERVO CAPSTAN.  THE LOCATING PIN LOCKED THE AILERONS AT FULL DEFLECTION AGAINST THE CAPSTAN GUARD.  THIS CONDITION OCCURRED ON THE GROUND, IN FLIGHT THIS CONDITION WOULD VERY LIKELY RESULT IN AN ACCIDENT.  RECOMMEND ROLL SERVO INSTALLATIONS BE INSPECTED FOR PROPER INSTALLATION AND RIGGING.  THE CONDITION HAS BEEN CORRECTED IAW FLIGHT DOCUMENT AK 1056.  (K)                                                                             1L71 3O3  O  A12SO   1E10                 
20060517002092006051700209SO  2006       5          17         2006FA0000481    220060425G8530646743          PISTON                                  MOONEYM20   M20K        5870220SW  CONT  O360  TSIO360SB        SO                              ENGINE          ERODED          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM0743PG 700                    252019                                  THE OIL CONTROL RING LANDS ON PISTON SEVERLY ERRODED AT PISTON PIN HOLE, BOTH SIDES OF PISTON.  THIS IS THE 13 TH PISTON THAT WE HAVE SEEN THIS ON, IN OUR ENGINE SHOP.  SC MODIFICATIONS, HAS 12 OF THEM, HAVE SAME PROBLEM.  HAVE ONE TO SHOW. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L71 3O3  O  2A3     E9CE                 
20060516002102006051600210    2006       5          16         2006FA0000482    420060501G2562EBC502          ELT                                     DIAMONDA20  DA20A1      2990000GL                                                               BAGGAGE COMPT   MISINSTALLED    B  UKJRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA2371LV                        10070                                   WHEN REMOVING ELT FROM AIRCRAFT TO REPLACE ELT BATTERY, FOUND THAT SOMEONE HAD PUT THE ELT IN BACKWARDS.  THE DIRECTION OF FLIGHT ARROW WAS POINTING AFT.  THIS INSTALLATION IS LOCATED IN THE BAGGAGE COMPT AND THE PILOT CAN SLIDE IT OUT OF ITS MOUNT AND REINSTALLED IT BACKWARDS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L71 3O    NTTA4CH                        
20070511001552007051100155SW  2007       5          11         2006FA0000483    120060428G62103G62200A251     BOLT                                    AGUSTAAB139 AB139       0260110SW                                                               MAIN ROTOR      GOUGED          B  LWXRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW19140HS8                      31036                                   UPON RECEIPT OF THE AIRCRAFT, THE MAIN ROTOR BLADE BOLTS WERE REMOVED FOR INSPECTION.  IT WAS DISCOVERED THAT ONE BLADE BOLTS HAS A RADIAL GOUGE MARK AT THE LOWER BLADE TO HUB BUSHING LOCATION.  THE DAMAGE IS OUTSIDE THE AMM PERMITTED REPAIR LIMITS.  THE AC TT IS APPROXIMATELY 58.4 HOURS.  ALL OF THE BLADE BOLTS WERE PREVIOUSLY CHANGED APPROX 8.5 HOURS PRIOR TO COMING TO REPAIR STATION.  REF: 39A62221300A286AB, MFG HAS BEEN CONTACTED AND PROVIDED THIS INFORMATION.  (K)                                                                                                                                                                                                                                                       2G72 6U      R00002RD                     
20060518001812006051800181CE  2006       5          18         2006FA0000484    120060223G57435041000201      TRUNNION                                CESSNA402   402B        207590PCE                                                               LT WING         BROKEN          G      K   NONE                                                                                            O  OTHER                                                                         LDLANDING        1                      SO19400AR2300                   402B0338                                ON FEBRUARY 23RD, 2006, PILOT WAS OPERATING AC, VISUAL FLIGHT RULES PREVAILED.  UPON LANDING, THERE WAS A FAILURE OF THE TRUNNION (P/N 5041000-201) ON THE LT MAIN LANDING GEAR STRUT CAUSING THE COLLAPSE OF THE LT MAIN LANDING GEAR.  THE AIRCRAFT TURNED 180 DEGREES TO THE LT AND SLID OFF THE LT SIDE OF RUNWAY 27L, CAUSING DAMAGE TO THE LT WING, HORIZONTAL STABILIZER AND LT PROPELLER.                                                                                                                                                                                                                                                                                                                                               1L72 3O      A7CE                         
20060516002112006051600211CE  2006       5          16         2006FA0000485    120060511G2742071250013       JACKSCREW                               CESSNA185   A185F       2072821CE                                                               TRIM SYS        STRIPPED        G      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL01275328672                   18503688                                MAINTENANCE PERSONNEL WERE ADVISED BY THE PILOT THE HORIZONTAL STABILIZER TRIM QUIT WORKING.  INSPECTION FOUND THE BARREL SIDE OF THE TRIM SCREW JACK HAD STRIPPED OUT.  THE SYSTEM INCLUDES 2 TRIM SCREW JACKS THE OTHER TRIM SCREW JACK TOOK ALL OF THE LOAD AND JAMMED UP.  INSPECTION OF SECOND TRIM SCREW JACK BARREL FOUND THE UPPER THIRD OF THE THREADS WERE STRIPPED IN THE SECOND TRIM SCREW BARREL.  MFG DOES NOT SPECIFY ANY INSPECTION CRITERIA FOR WEAR OF THE JACK SCREW THREADS OR THE BARREL THREADS.  RECOMMEND EITHER MANDATORY INSPECTION CRITERIA FOR THE BARRELS AND THREADS OR AN AIRWORTHINESS DIRECTIVE TO PRECLUDE LOSS OF CONTROL OF THE TAIL OF THE AIRCRAFT.  (K)                                                  1H71 3O      3A24                         
20060518002632006051800263CE  2006       5          18         2006FA0000486    120060511G2821331996          GASKET                                  BEECH 58    58          1152740CE                                                               WHEEL WELL      SWOLLEN         D      K   NONE                                                                                            K  FLUID LOSS                                                                    CRCRUISE         1                      WP152335R                       TH1835                                  THE FUEL FILTER GASKETS SWELLED CAUSING THE FUEL FILTERS TO LEAK A LARGE AMOUNT OF FUEL OB WHILE IN FLIGHT. THE PILOT WAS UNAWARE OF THE LOSS OF FUEL UNTIL AFTER LANDING.  APPARENTLY GASKETS ARE NOT COMPATIBLE WITH CURRENT BLENDS OF 100LL. WAS TOLD BY MFG TECHS THAT LOCAL AVGAS MAY HAVE LARGER AMOUNTS OF BENZENE AND TOULENE AND MAY BE CAUSING THE SWELLING OF THE GASKETS. THIS PROBLEM HAS OCCURRED MULTIPLE TIMES. PROBLEM UNRESOLVED AT THIS TIME.                                                                                                                                                                                                                                                                                1L72 3O      3A16                         
20060518002652006051800265CE  2006       5          18         2006FA0000487    120060511G2821331996          GASKET                                  BEECH 58    58          1152740CE                                                               WHEEL WELL      SWOLLEN         D      K   NONE                                                                                            K  FLUID LOSS                                                                    CRCRUISE         1                      WP152335R                       TH1835                                  THE FUEL FILTER GASKETS SWELLED CAUSING THE FUEL FILTERS TO LEAK A LARGE AMOUNT OF FUEL OVERBOARD WHILE IN FLIGHT. THE PILOT WAS UNAWARE OF THE LOSS OF FUEL UNTIL AFTER HE LANDED.  APPARENTLY GASKETS ARE NOT COMPATIBLE WITH CURRENT BLENDS OF 100LL. WAS TOLD BY MFG TECHS THAT LOCAL AVGAS MAY HAVE LARGER AMOUNTS OF BENZENE AND TOULENE AND MAY BE CAUSING THE SWELLING OF THE GASKETS. THIS PROBLEM HAS OCCURRED MULTIPLE TIMES. PROBLEM UNRESOLVED AT THIS TIME.                                                                                                                                                                                                                                                                       1L72 3O      3A16                         
20060518002672006051800267CE  2006       5          18         2006FA0000488    120060511G2821331996          GASKET                                  BEECH 58    58          1152740CE                                                               WHEEL WELL      SWOLLEN         D      K   NONE                                                                                            K  FLUID LOSS                                                                    CRCRUISE         1                      WP152335R                       TH1835                                  THE FUEL FILTER GASKETS SWELLED CAUSING THE FUEL FILTERS TO LEAK A LARGE AMOUNT OF FUEL OVERBOARD WHILE IN FLIGHT. THE PILOT WAS UNAWARE OF THE LOSS OF FUEL UNTIL AFTER HE LANDED. APPARENTLY GASKETS ARE NOT COMPATIBLE WITH CURRENT BLENDS OF 100LL. WAS TOLD BY RAYTHEON TECHS THAT LOCAL AVGAS MAY HAVE LARGER AMOUNTS OF BENZENE AND TOULENE AND MAY BE CAUSING THE SWELLING OF THE GASKETS. THIS PROBLEM HAS OCCURRED MULTIPLE TIMES. PROBLEM UNRESOLVED AT THIS TIME.                                                                                                                                                                                                                                                                   1L72 3O      3A16                         
20060518002722006051800272SO  2006       5          18         2006FA0000489    220060503G8530AEC631397       CYLINDER                                BEECH 36    A36         1151604CE  CONT  O550  IO550B           SO  MCAULY3A32C D3A32C*     GL  ENGINE          SEPARATED       B  MW8RK   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      SO018277D                       E2798       G675825     930397          NR 2 CYLINDER HEAD (SN 2253724) SEPARATION WITH 170.2 TOTAL SINCE NEW.  NR 6 CYLINDER HEAD (SN 223899) SEPARATION WITH 171.7 TOTAL SINCE NEW.  AD 2004-08-10 N/A TO SN.  RECOMMEND ALL SN`S APPLICABLE AND REOCCURING CHECKS FOR ECI CYLINDERS USING M 91-6.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L71 3O3  O  3A15    E3SO    5  CP21EA    
20060517002132006051700213SW  2006       5          17         2006FA0000490    120060302G29135001908         COUPLING                                BELL  206   206B        1181511SW  ALLSN 250C  250C20      03013GL                              HYD PUMP        SEPARATED       B  YJ2RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP0137AJ            00010491    1877                                    HYDRAULIC PUMP TACH DRIVE COUPLING BRAZED WELDING FAILED CAUSING COUPLING TO SEPARATE FROM DRIVE GEAR SHAFT.  MFG SHOULD CHECK THE STRENGTH OF BRAZE AFTER WELDING.  WHEN THIS COUPLING FAILS, LOSS OF ROTOR TACH OCCURS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1G71 3U3  U  H2SW    E4CE                 
20060518002792006051800279SW  2006       5          18         2006FA0000491    120060302G29135001908         COUPLING                                BELL  206   206B        1181511SW  ALLSN 250C  250C20B     03013GL                              HYD PUMP        FAILED          B  XJ2RK   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      WP0159479196        99100424    1194                                    HYDRAULIC PUMP TACH DRIVE COUPLING BRAZED WELDING FAILED CAUSING COUPLING TO BECOME LOOSE.  MFG SHOULD CHECK THE STRENGTH OF BRAZE AFTER WELDING.  WHEN THIS COUPLING FAILS, LOST OF ROTOR TACH OCCURS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1G71 3U3  U  H2SW    E4CE                 
20060517002142006051700214SW  2006       5          17         2006FA0000492    120060302G29135001908         COUPLING                                BELL  206   206B        1181511SW                                                               HYD PUMP        FAILED          B  XJ2RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP01158H            00010463    2974                                    HYDRAULIC PUMP TACH DRIVE COUPLING BRAZE WELDING FAILED, CAUSING COUPLING TO SEPARATE FROM DRIVE GEAR SHAFT.  MFG SHOULD CHECK THE STRENGTH OF BRAZE AFTER WELDING.  WHEN THIS COUPLING FAILS, LOSS OF ROTOR TACH OCCURS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1G71 3U      H2SW                         
20060519002502006051900250CE  2006       5          19         2006FA0000493    120060504G574050110231        FITTING                                 CESSNA414   414         2075908CE  CONT  O520  TSIO520*    17040SO                              LT WING         CRACKED         B  AIHRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL11352TS3751                   4140352                                 DURING ANNUAL INSP FOUND LT STUB WING AFT SPAR, UPPER FITTING CRACKED AT OB BOLT HOLE.  FOUND NO CORROSION OR STRESS IN SURROUNDING AREAS.  SUSPECT BOLT WAS OVERTORQUED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L72 3O3  ORTA7CE    E8CE                 
20060517002302006051700230CE  2006       5          17         2006FA0000494    120060426G7160                AIR BOX                                 CESSNA172   172P        2072436CE  LYC   O360  O360A4M     41514EA                              ENGINE          MAINT ERROR     B  BIIRK   NONE                                                                                            R  PARTIAL RPM/PWR LOSS                                                          CRCRUISE         1                      EA21657641443 231               17275868    RL3482936A                  AC HAD 180 HP ENGINE INSTALLED ON 7/10/96.  AC HAS 1443.5 HOURS SINCE INSTALLATION.  OPERATOR NOTED 2300 RPM AT CRUISE, FULL THROTTLE.  INSPECTED AND FOUND AIRBOX STILL HAD THE HOLE SIZE FOR 160 HP ENGINE.  AIRBOX HAD NOT BEEN MODIFIED IAW STC. IT HAD BEEN REPAIRED ON SEVERAL OCCASIONS SINCE ENGINE INSTALLED AND HAD NOT BEEN FOUND.  (K)                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O3  ONT3A12    E286                 
20060517002312006051700231EA  2006       5          17         2006FA0000495    220060509G8550CH481101        OIL FILTER                              PIPER PA28  PA28R201    7102816SO  LYC   O360  IO360C1C    41514EA                              ENGINE          LEAKING         B  JULRK   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      SW011663H                       28R7737007  RL723851A                   PILOT REPORTED OIL SPOTS ON HANGAR FLOOR.  ENGINE WAS WASHED AND GROUND RUN FOR LEAK CHECK.  INSPECTED ENGINE AFTER ENGINE RUN AND FOUND OIL ON BOTTOM SIDE OF OIL FILTER.  FURTHER INSPECTION OF THE OIL LEAK REVEALED THAT THE OIL WAS LEAKING FROM THE HEX NUT ON THE BACK OF THE FILTER.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                               1L71 3O3  O  2A13    1E10                 
20060519002512006051900251EU  2006       5          19         2006FA0000496    120060505G6210355A11002011    BLADE                                   SNIAS 350   AS350B      8680801EU  TMECA ARRIELARRIEL1     60030NE                              MAIN ROTOR      CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW095806H                       1935                                    CRACK FOUND ON LOWER SURFACE OF MAIN ROTOR BLADE NEAR STATION 1000.  EXACT CAUSE OF CRACK WOULD ONLY BE SPECULATIVE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1G71 3U3  U  H9EU    E19EU                
20060518000692006051800069CE  2006       5          18         2006FA0000497    120060509G5310551124914S      THRESHOLD                               CESSNA500   560CESSNA   2076750CE  PWA   JT15  JT15D5      52112NE                              CABIN DOOR FRAMECRACKED         B  JGVRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09318QS8377                   5600418                                 CABIN ENTRY THRESHOLD CRACKED AT AFT STEP ATTACH BOLT HOLE.  COMBINATION OF BOLT HOLE LOCATED IN RADIUS OF FRAME AND MATERIAL THICKNESS NOT SUFFICIENT TO SUPPORT WEIGHT OF PERSON ENTERING OR EXITING AIRCRAFT.  RECOMEND STRENGTHING STRUCTURE, USING THICKER METAL.  NOTE: HAVE FOUND THESE CRACKS ON MFG INSPECTION PHASE 5.  APPROX 75 PERCENT OF AIRCRAFT INSPECTED ARE FOUND CRACKED.  (K)                                                                                                                                                                                                                                                                                                                                               2L72 4F4  FRTA22CE   E25EA                
20060518000382006051800038SO  2006       5          18         2006FA0000498    220060511G8530AEC631397       CYLINDER                                CESSNA414   414         2075908CE  CONT  O520  TSIO520NB   17040SO                              ENGINE          CRACKED         D      K   NONE                                                                                            E  VIBRATION/BUFFET                                                              DEDESCENT        1                      GL13710US330                    4140083     519719                      DURING DECENT TO AIRPORT, PILOT REPORTED RT ENGINE STARTED HAVING EXCESSIVE VIBRATION.  NO OTHER MAJOR ENGINE INDICATIONS WERE NOTED.  AFTER LANDING, A MAGNETO CHECK WAS CONDUCTED AND NO DESCREPANCIES WERE FOUND.  UPON REMOVAL OF COWLING, RT ENGINE NR 6 CYLINDER WAS FOUND TO HAVE CRACKED AROUND THE CIRCUMFERENCE OF CYLINDER HEAD AT THE NR 9 AND 10 COOLING FIN, COMPLETELY SEPARATING THE CYLINDER HEAD FROM THE BARREL AT THE VERY TOP OF STEEL CYLINDER BARREL.  AFTER RESEARCHING AD, AMENDMENT, THE CYLINDER ASSY WAS FOUND NOT TO APPLY DUE TO S/N OF CYLINDER AND THE PRESENCE OF THE (A) STAMPED ON THE ROCKER BOX FLANGE.  (K)                                                                                               1L72 3O3  ORTA7CE    E8CE                 
20060517002062006051700206SO  2006       5          17         2006FA0000499    220060411G8530641916A1        CYLINDER                                CESSNA172   172D        2072410CE  CONT  O300  O300D       17022SO                              ENGINE          CRACKED         C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NE032566Y     1432              17249866    27538                       NR 1 CYLINDER WAS REMOVED DUE TO A CRACK .75 AROUND STEEL BARREL.  IT APPEARS THAT AN OIL CONTROL RING BROKE AND EVENTUALLY DESTROYED THE PISTON AND JAMMED BETWEEN THE PISTON AND CYLINDER.  TT ON THE ENGINE IS 4156.9 HRS.  SMOH IS 1432.9 HRS, THE CYLINDER WAS LAST REMOVED AT 598.4 HOURS FOR HONE AND NEW RINGS.  TT ON CYLINDERS, UNKNOWN.  AIRCRAFT WAS ANNUALED 1.1 HRS PRIOR.  THE OIL ANALYSIS PERFORMED AT ANNUAL WAS NORMAL AND ALL READINGS/RESULT WERE LOWER THAN THAT OF PREVIOUS AVIATION LABORATORY SAMPLES WHICH WERE ALSO NORMAL.  ENGINE WILL BE TORN DOWN FOR INTERNAL INSPECTION.  (K)                                                                                                                                  1H71 3O3  ONT3A12    E253                 
20060519002432006051900243SW  2006       5          19         2006FA0000500    120060428G5711271L            SPAR                                    BBAVIA7     7GCBC       1220601SW  LYC   O320  O320*       41508EA                              LT WING         CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL1588237                       74474                                   DURING WING RECOVER, FOUND LT WING FRONT SPAR WITH A CRACK ORIGINATING AT THE BUTT END, FOLLOWING THE WOOD GRAIN OB THROUGH UPPER ATTACH BRACKET HOLES AND EXTENDING APPROXIMATELY 1 INCH PAST IB MOST FUEL TANK SUPPORT BRACKET, UPPER HOLE.  NO EVIDENCE OF CRACKS IN BUTT ENG SPAR DOUBLERS.  TOTAL LENGTH OF CRACK APPROX 8.3750 INCHES.  NO RECOMMENDATION FOR CAUSE OR RECURRENCE.  (K)                                                                                                                                                                                                                                                                                                                                                   1H71 3O3  ONCA759    E274                 
20060518001382006051800138NM  2006       5          18         2006FA0000501    120060516G7921900D3658501103  OIL COOLER                              DOUG  MD900 MD900       3027375NM  PWC   PW207 PW207E           NE                              ENG OIL SYS     LEAKING         D      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      EA11902PD589                    9000084                                 FOUND WETTING OIL MAIN TRANSMISSION/ENGINE OIL COOLER CORE. REMOVED AND SENT OUT FOR EVALUATION. COOLER FOUND TO HAVE INTERNAL CORROSION THAT CAUSED MATERIAL LOSS AND SUBSEQUENT LEAKING. REPLACED COOLER WITH NEW. LEAK CHECK WAS SATISFACTORY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1G72 3U3  UNCH19NM   E42NE                
20060518002662006051800266SO  2006       5          18         2006FA0000502    120060503G29101159SCH5019     SHUTOFF VALVE                           GULSTMGV    GULFSTREAMGV3980116SO  RROYCEBR700 BR700710A110     NE                              LT & RT WING    MALFUNCTIONED   D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW05130GV2943                   630                                     DURING A SCHEDULED INSPECTION, OPERATIONAL CHECK OF THE AILERON HARD OVER PROTECTION TEST.  BOTH LT AND RT AILERON HYD SHUT OFF CIRCUIT BREAKERS POPPED.  REPLACED RT AILERON , LT HYD SYSTEM SHUTOFF VALVE AND LT AILERON, LT HYD SYS SHUTOFF VALVE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F4  FRTA12EA   E00057EN             
20060518002302006051800230NM  2006       5          18         2006FA0000503    120060516G632051003400        HOSE                                    DOUG  MD900 MD900       3027375NM  PWC   PW207 PW207E           NE                              MAINTRANSMISSIONCRACKED         D      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      EA11902PD489                    9000084                                 DISCOVERED MAIN TRANSMISSION OIL HOSE FROM OIL COOLER TO MAIN TRANSMISSION LEAKING FROM STEEL BRAIDING. PULLED BACK BRAIDING AND FOUND HOSE TO BE CRACKED. REPLACED LINE WITH NEW. LEAK CHECK OF NEW LINE WAS SATISFACTORY, P/N 900D3409526-105.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1G72 3U3  UNCH19NM   E42NE                
20060518002562006051800256GL  2006       5          18         2006FA0000504    120060508G552410146008        RIVET                                   CIRRUSSR    SR22        2130001GL  CONT  O550  IO550N      17042SO                              ELEVATOR        LOOSE           D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP155226R                       1767                                    BOTH LT AND RT ELEVATOR OB HINGE BRACKETS ARE RIVETED TO THE ELEVATORS WITH FLUSH HEAD BLIND RIVETS AND FLUSH HEAD SOLID DRIVE RIVETS.  AT 121 HOURS TT.  DURING A 100 HOUR INSPECTION, THE RIVETS ON THE OB HINGE BRACKETS, LT AND RT ELEVATORS, WERE FOUND TO BE SMOKING- STREAKS OF BLACK POWDER TRAILING BEHIND THEM, AND THE PAINT AROUND THE RIVET HEADS BROKEN.  RECOMMEND MFG DESIGN FIND A SECURE WAY TO HOLD THE ELEVATOR HINGE BRACKETS TO THE ELEVATORS SUCH AS THROUGH USE OF SOLID-DRIVEN RIVETS INSTEAD OF BLIND RIVETS.  (K)                                                                                                                                                                                                    1L71 3O3  ONTA00009CHE3SO                 
20060518001962006051800196NM  2006       5          18         2006FA0000506    120060516G632051003400        HOSE                                    DOUG  MD900 MD900       3027375NM  PWC   PW207 PW207E           NE                              MAIN TRANSMSN   CRACKED         D      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      EA11902PD489                    9000084                                 DISCOVERED MAIN TRANSMISSION OIL HOSE FROM OIL COOLER TO MAIN TRANSMISSION LEAKING FROM STEEL BRAIDING. PULLED BACK BRAIDING AND FOUND HOSE TO BE CRACKED. REPLACED LINE WITH NEW. LEAK CHECK OF NEW LINE WAS SATISFACTORY.  P/N 900D3409526-105.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1G72 3U3  UNCH19NM   E42NE                
20060518000572006051800057NM  2006       5          18         2006FA0000507    120060516G6220900R1103001113  BEAM                                    DOUG  MD900 MD900       3027375NM  PWC   PW207 PW207E           NE                              MR HUB          CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA11902PD1898 100               9000084                                 DURING SCHEDULED INSPECTION FOUND FLEXBEAM CRACKED IN LEG OF FLEXBEAM. REJECTED FLEXBEAM IAW INSPECTION CRITERIA IN MAINTENANCE MANUAL. REPLACED WITH NEW FLEXBEAM.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1G72 3U3  UNCH19NM   E42NE                
20060518002462006051800246NM  2006       5          18         2006FA0000508    120060516G6220900R1103001113  BEAM                                    DOUG  MD900 MD900       3027375NM  PWC   PW207 PW207E           NE                              MR HUB          CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA11902PD1898 100               9000084                                 DURING SCHEDULED INSPECTION FOUND FLEXBEAM CRACKED IN LEG OF FLEXBEAM. REJECTED FLEXBEAM IAW INSPECTION CRITERIA IN MM. REPLACED WITH NEW FLEXBEAM.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1G72 3U3  UNCH19NM   E42NE                
20060530001752006053000175SW  2006       5          30         2006FA0000509    120060513G6720500N72205       CABLE                                   HUGHES500N  500N        3027374SW                                                               TAILBOOM        SEVERED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP05520HB                       LN029                                   DURING PRACTICE AUTOROTATIONS, PILOT FELT A CHANGE IN THE ANTI-TORQUE PEDALS. AFTER TOUCHDOWN HE ATTEMPTED TO RAISE THE COLLECTIVE AND THE HELICOPTER BEGIN TO SPIN, HE LOWERED THE COLLECTIVE AND SHUTDOWN. NO DAMAGE WAS NOTED. THE ROTATING CONE CONTROL CABLE WAS FOUND TO HAVE A CLEAN BREAK. THE OTHER CABLES WERE INSPECTED AND FOUND TO BE OK. P/N 500N7220-05 WAS INSPECTED AT THE LAST 300HR INSPECTION 232.8 HOURS AGO, AND WAS FOUND TO BE AIRWORTHY. THIS PART DOES NOT HAVE A SERVICE LIFE LIMIT FROM THE MFGR. RECOMMEND A SERVICE LIFE OF 1000 HOURS.                                                                                                                                                                           1G71 3U    NCH3WE                         
20060522001722006052200172SO  2006       5          22         2006FA0000510    120060421G3220402940          BOLT                                    PIPER PA44  PA44180     7104402SO                                                               NOSE GEAR       BROKEN          B  NI1RK   NONE                                                                                            O  OTHER                                                                         LDLANDING        1                      CE03554PC                       4496073                                 NOSE GEAR COLLAPSED ON TOUCHDOWN.  MAINS TOUCHED FIRST THEN NOSE.   2 COMPONENTS THAT ARE DAMAGED IN NOSE GEAR RETRACT/EXTEND SYS.  W/O DISASSEMBLING LINKAGE, VISUAL EVIDENCE, BOLT CONNECTING UPPER DRAG LINK TO LWR DRAG LINK FAILED DUE TO POSSIBLE OVERLOAD CONDITION.  (FRACTURED END OF BOLT IS BRIGHT AND SHINNY, INDICATING AN INSTANTANEOUS FAILURE).  ONE HALF OF THAT BOLT, WASHER, NUT AND COTTER PIN IS STILL INSERTED IN JOINT.  OTHER DAMAGED COMPONENT IS BOLT THAT DOWNLOCK HOOK ENGAGES, BOLT IS BENT IN SUCH A WAY AS TO INDICATE IT WAS DAMAGED AS A RESULT OF NOSE GEAR COLLAPSE.  AFTER UPPER AND LWR DRAG LINK ASSEMBLIES HAVE BEEN REMOVED SENT TO MFG FOR FURTHER INSP AND ANALYSIS.                                  1L72 3O      A19S0                        
20060522001422006052200142CE  2006       5          22         2006FA0000511    120060504G79209696001123      LINE                                    BEECH 58    58          1152740CE  CONT  O550  IO550C           SO                              ENGINE          CHAFED          D      E   ENGINE SHUTDOWN                                                                                 JK WARNING INDICATION        FLUID LOSS                                          CRCRUISE         1                      EA13251P                        TH2139      686637                      2 LINES CHAFFING TOGETHER.  NEED TO SEPARATE THE LINES.  LOW OIL PSI IN FLIGHT.  PILOT SHUTOFF ENGINE IN FLIGHT AND LANDED THE AIRCRAFT.  REMOVED AND REPLACED THE LINE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1L72 3O3  O  3A16    E3SO                 
20060522001442006052200144    2006       5          22         2006FA0000512    420060421G342570000006000     FLIGHT DIR                              CIRRUSSR    SR22        2130001GL                                                               COCKPIT         FAILED          D  OBKRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL13629LF                       0843                                    PFD WAS JUST UPDATED TO REV 6.  2 DAYS AFTERWARDS, SCREEN WOULD FAIL IN FLIGHT.  DISPLAY WOULD FLICKER AND NOT BE USABLE.  UNIT WOULD ALSO FAIL TO BOOT UP IN HANGAR.  CUSTOMER WAS GIVEN EXCHANGE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L71 3O    NTA00009CH                     
20060522001702006052200170    2006       5          22         2006FA0000513    420060404G342570000006000     FLIGHT DIR                              CIRRUSSR    SR22        2130001GL                                                               COCKPIT         FAILED          D  OBKRK   NONE                                                                                            O  OTHER                                                                         CRCRUISE         1                      GL13623KT                       0486                                    THIS PARTICULAR PFD HAD 3 BACK TO BACK FAILURES THAT COULD ONLY BE DETECTED AFTER 1 HOUR + OF FLIGHT.  DISPLAY WOULD LIGHTEN UP, TURN GREEN AND FLICKER.  WOULD NOT BE USABLE.  THIS UNIT WAS UPGRADED TO REV 6 SOFTWARE FOR FLIGHT DIRECTOR.  FAILURES HAPPENED AFTER THIS MOD.  FAILURES HAPPENED AFTER THIS MOD UNIT WAS SENT TO MFG AFTER FIRST 2 FAILURES, THIRD FAILURE RESULTED IN AN EXCHANGE.  (1ST-3-6-06-W/O AVO6-6617) (2ND - 3-29-06, W/O AVO6-6658) (3RD-4-4-06 W/O AVO6-6687)                                                                                                                                                                                                                                                    1L71 3O    NTA00009CH                     
20060522001502006052200150SO  2006       5          22         2006FA0000514    220060420G8530                CYLINDER                                CESSNA210   T210N       2073456CE  CONT  O520  IO520L      17032SO                              ENGINE          ERODED          D      E   ENGINE SHUTDOWN                                                                                 E  VIBRATION/BUFFET                                                              CRCRUISE         1                      CE015337Y           517945      21064171    517945                      FOUND NR 6 PISTON ERODED FROM POSSIBLE DETONATION BY UNKNOWN CAUSES.  FOUND NR5 CYLINDER CONNECTING ROD CAP MISSING AND INTERNAL DAMAGE TO THE CRANKCASE.  NO OIL WAS NOTED ON THE DIPSTICK PRESUMED TO BE FORCED OUT OF THE ENGINE DUE TO EXCESSIVE BLOW BY FROM THE ERODED NR 5 CYL.  THE ENGINE WAS SHUT DOWN AND LANDED IN A GRASS FIELD WITH NO DAMAGE TO THE AIRCRAFT.  (K)                                                                                                                                                                                                                                                                                                                                                               1H71 3O3  O  3A21    E5CE                 
20060522001732006052200173    2006       5          22         2006FA0000515    420060505G2562                ELT                                     CESSNA210   2105        2073404CE                                                               FUSELAGE        FAILED          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL098197Z                       2050197                                 ELT FAILED UPON INSPECTION AFTER 12 MONTHS OF SERVICE, DID NOT TRANSMIT THROUGH ANTENNA, LIGHT WENT ON INDICATING FUNCTION.  THIS IS THE 3RD FAILURE ON UNITS NEWER THAN ONE YEAR OLD, IN 1.5 YEARS IN OUR SHOP.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1H71 3O      3A21                         
20060522001542006052200154    2006       5          22         2006FA0000516    420060306G2562AK450           ELT                                     HUGHES269   269A        4470402WP  LYC   O360  IO360A1A    41514EA                              FUSELAGE        FAILED          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL0962273                       291096                                  ELT FAILED UPON INSPECTION AFTER EIGHT MONTHS OF SERVICE, DID NOT TRANSMIT THOUGH ANTENNA, LIGHT WENT ON INDICATING FUNCTION.  THIS IS THE SECOND TIME THIS HAS FAILED THIS YEAR.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1G71 3O3  O  4H12    1E10                 
20060522001662006052200166    2006       5          22         2006FA0000517    420060306G2562AK450           ELT                                     HUGHES269   269A        4470402WP                                                               FUSELAGE        FAILED          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL0962273                       291096                                  ELT FAILED UPON INSPECTION AFTER NINE MONTHS OF SERVICE.  DID NOT SWEEP.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1G71 3O      4H12                         
20060522001712006052200171GL  2006       5          22         2006FA0000518    120060505G8011                SOLENOID                                CIRRUSSR    SR22        2130001GL  CONT  O550  IO550N      17042SO                              STARTER         INTERMITTENT    B  LC1RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA07343CD399                    1343        917602                      THE STARTER ON THIS AIRCRAFT FAILED.  THIS IS THE THIRD FAILURE OF THIS TYPE STARTER HAS A SOLENOID ATTACHED AND THE PROBLEM NOTED IS THAT THIS SOLENOID BECOMES INTERMITTENT. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L71 3O3  ONTA00009CHE3SO                 
20060522001472006052200147CE  2006       5          22         2006FA0000519    120060331G3233508202085       ACTUATOR                                BEECH 200   200BEECH    1152920CE                                                               NOSE GEAR       UNSERVICEABLE   D      O   OTHER                                                                                           J  WARNING INDICATION                                                            LDLANDING        1                      GL11641TS                       BB641                                   AIRCRAFT NOSE WHEEL FAILED TO EXTEND WHEN GEAR SELECTOR WAS PLACED IN DOWN POSITION.  NOSE GEAR WAS OBSERVED BY TOWER PERSONNEL TO BE PARTIALLY EXTENDED BUT NOT LOCKED DOWN.  PILOT ATTEMPTED EMERGENCY EXTENSION WITHOUT SUCCESS.  AIRCRAFT LANDED ON MAIN GEAR AND SLOWED AS MUCH AS POSSIBLE BEFORE LOWERING NOSE TO GROUND.  AIRCRAFT SUSTAINED VERY LITTLE DAMAGE UPON LANDING.  ENGINES WERE SHUT DOWN AND PROPELLERS FEATHERED PRIOR TO LOWERING NOSE.  DAMAGE WAS CONTAINED TO RAYDOME, PITOT TUBES, NOSE GEAR DOORS AND PROPELLERS.  AIRCRAFT WAS FURTHER DAMAGED DURING RECOVERY PHASE WHEN HOISTING STRAP BROKE AND AIRCRAFT FELL BACK TO GROUND APPROX 4 FEET CAUSING STRUCTURE DAMAGE TO AFT FUSELAGE BEHIND PRESSURE BULKHEAD.   1L72 4T      A24CE                        
20060523002312006052300231EA  2006       5          23         2006FA0000521    220060518G8520LW13820         CRANKCASE       LYC         O360A4M     CESSNA172   172N        2072434CE  LYC   O360  O360A4M     41514EA                              ENGINE          CRACKED         D      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      EA071962F4956 1460  L1726436A   17273052    L1726436A                   DURING A 100 HR INSPECTION, AN OIL LEAK WAS NOTED AROUND THE L/H FORWARD CRANKCASE AROUND THE UPPER CRANKCASE BOLT (PN 6-34A WITH PN LW-11866 NUT).  THE ENGINE WAS CLEANED AND A DYE PENETRANT INSPECTION PERFORMED.  A CRACK ROUGHLY 4 INCHES LONG WAS FOUND RUNNING VERTICALLY ON THE CRANKCASE FROM ABOUT 1 INCH BELOW THE CRANKCASE SEAM DOWN TO THE EDGE OF THE BEARING SURFACE OF THE BOLT HOLE, THEN DOWN ANOTHER 3 INCHES.  THE ENGINE IS BEING REMOVED FOR REPAIR OF CRANKCASE (IF POSSIBLE) OR REPLACEMENT.                                                                                                                                                                                                                          1H71 3O3  ONT3A12    E286                 
20060522002002006052200200CE  2006       5          22         2006FA0000522    120060522G2424UAM100          CURRENT LIMITER RAYTHN                  RAYTHNDH125 HAWKER800XP 7150012CE  GARRTTTPE331TPE331*     01514WP                              ELECT PANEL     MISDRILLED      B      K   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      SW11875QS                       258375                                  MOUNTING HOLES IN CURRENT LIMITER DOES NOT MATCH LUGS IN ELECTRICAL PANEL.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F3  TRTA3EU    E2WE                 
20060523002322006052300232CE  2006       5          23         2006FA0000523    120060520G5500550             SKIN            CESSNA                  CESSNA500   550         2076604CE                                                               EMPENNAGE       CORRODED        B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW171255K           0505        5500505                                 AFTER A PHASE 1,2,3,4,49&59 CORROSION AND DELAMINATION WAS FOUND ON TOP AND BOTTOM SKINS LT AND RT SIDES OF THE HORIZONTAL STABILIZER, LT SKIN OF THE VERTICAL STABILIZER. TAIL SKINS 5512010-9 AND 6512010-20 (SKINS UNDER VERT. STAB.) AS WELL AS THE AFT BULKHEAD 6412016-1SP WERE REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L72 4F      A22CE                        
20060523002332006052300233CE  2006       5          23         2006FA0000524    120060521G37101U478003        PUMP            CONT                    BEECH 33    F33A        1151425CE                                                               ENGINE          BROKEN          D      O   OTHER                                                                                           IG FLT. ATTITUDE INST.       MULTIPLE FAILURE                                    CRCRUISE         1                      GL1911BX 219                    CE388                                   VACUUM PUMP FAILURE INFLIGHT - FIRST NOTICED ATTITUDE CHANGE (STARTED DECENDING RAPIDLY) (AUTOPILOT ENGAGED)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L71 3O      3A15                         
20060523002352006052300235CE  2006       5          23         2006FA0000525    120060520G55205534000204      ELEVATOR        CESSNA                  CESSNA500   550         2076604CE                                                               RT ELEVATOR     MAINT ERROR     B      L   ABORTED APPROACH                                                                                O  OTHER                                                                         ININSP/MAINT     1                      SW171255K9471                   0505                                    AFTER A REPAIR AT ANOTHER FACILITY THIS ELEVATOR WAS IN A BIND AND NOT ABLE TO STREAMILINE WITH THE STABILIZER (COULD NOT RIG). IT APPEARS THAT THIS CONTROL WAS NOT INSTALLED CORRECTLY IN A JIG FIXTURE. WHILE REPLACING THE UPPER AND LOWER SKINS IT WAS ALSO FOUND THAT THE FWD. SPAR WAS DAMAGED BY ALLOWING DRILL BITS TO GO THROUGH AND IMPACT ON THE SPAR. THIS CAUSED THE FWD. SPAR TO ALSO BE REPLACED.                                                                                                                                                                                                                                                                                                                               1L72 4F      A22CE                        
20060523002362006052300236CE  2006       5          23         2006FA0000526    120060520G5751                AILERON         CESSNA                  CESSNA500   550         2076604CE                                                               RT AILERON      CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW1743SA 9863                   0086                                    DURING A PHASE 1,2,3,4 INSPECTION THE RT AILERON WAS FOUND TO BE CRACKED AT THE LEADING EDGE IN THE AREA OF ATTACHMENT POINTS FOR THE WEIGHTS. THE SKIN WAS REMOVED AND REPLACED. HAD SEVERAL CRACKED AILERONS IN OUR OTHER AIRCRAFT BOTH LT AND RT CRACK IN THIS AREA. WE OPERATE A FLEET OF THESE AIRCRAFT AND LOOK AT THIS ON A 300HR. INSPECTION SCH.  THE CRACKS GO AROUND THE SCREW HOLES OR RADIATE OUT FROM THEM.                                                                                                                                                                                                                                                                                                                       1L72 4F      A22CE                        
20060523002372006052300237CE  2006       5          23         2006FA0000527    120060521G37101U478003        PUMP            CONT                    BEECH 33    F33A        1151425CE  CONT  O520  IO520B      17032SO                              ENGINE          FAILED          D      O   OTHER                                                                                           IG FLT. ATTITUDE INST.       MULTIPLE FAILURE                                    CRCRUISE         1                      GL1911BX 219                    CE388                                   VACUUM PUMP FAILURE INFLIGHT, FIRST NOTICED ATTITUDE CHANGE (STARTED DECENDING RAPIDLY) (AUTOPILOT ENGAGED).                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L71 3O3  O  3A15    E5CE                 
20060530001582006053000158SW  2006       5          30         2006FA0000528    120060518G5302                FITTING         BELL                    BELL  204   UH1H        1181407SW                                                               TAIL BOOM       CRACKED         H      K   NONE                                                                                            J  WARNING INDICATION                                                            ININSP/MAINT     1                      SO15     4000                                                           TAIL BOOM ATTACH FITTING CRACKED UPPER LEFT [TAIL BOOM SIDE]                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1G71 4U      EXPA1G71                     
20060530001592006053000159SW  2006       5          30         2006FA0000529    120060518G5302                FITTING         BELL                    BELL  204   UH1H        1181407SW                                                               TAIL BOOM       CRACKED         H      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15     4000                                                           TAIL BOOM ATTACH FITTING CRACKED UPPER LEFT [TAIL BOOM SIDE]                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1G71 4U      EXPA1G71                     
20060530001602006053000160SW  2006       5          30         2006FA0000530    120060518G5302                FITTING         BELL                    BELL  204   UH1H        1181407SW                                                               TAIL BOOM       CRACKED         H      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15     4000                                                           TAIL BOOM ATTACH FITTING CRACKED UPPER LEFT [TAIL BOOM SIDE]                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1G71 4U      EXPA1G71                     
20060530001612006053000161CE  2006       5          30         2006FA0000531    120060521G2424UAM100          CURRENT LIMITER                         RAYTHNDH125 HAWKER800XP 7150012CE                                                               ELECT REG SYS   FAILED          B      A   UNSCHED LANDING                                                                                 H  ELECT. POWER LOSS-50 PC                                                       TOTAKEOFF        1                      SW11203TM                       258653                                  CURRENT LIMITER BLOWN, CAUSING LOSS OF ELECTRICAL POWER                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F    RTA3EU                         
20060530001622006053000162SO  2006       5          30         2006FA0000532    120060521G2436UAM100          CURRENT LIMITER                         PIPER PA18  PA18        7101802SO                                                               ELECT REG SYS   FAILED          B      K   NONE                                                                                            H  ELECT. POWER LOSS-50 PC                                                       TOTAKEOFF        1                      SW11203T                        182317                                  CURRENT LIMITER BLOWN, CAUSING LOSS OF ELECTRICAL POWER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1H71 3O      1A2                          
20060530001642006053000164GL  2006       5          30         2006FA0000533    120060518G7810DC00015B        EXHAUST RISER                           DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO                              ENGINE          CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW19107TX52                     C0310                                   ON A 100HR INSP NR 2 EX RISER CRACKED AT FLANGE. THIS HAS BEEN FOUND ON A NUMBER OF AIRCRAFT OF THIS TYPE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L71 3O3  ONTTA4CH   E7SO                 
20060522002412006052200241GL  2006       5          22         2006FA0000534    120060518G7810DC00015B        EXHAUST RISER                           DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO                              ENGINE          CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW19107TX52                     C0310                                   ON A 100HR INSP #2 EX RISER CRACKED AT FLANGE. THIS HAS BEEN FOUND ON A NUMBER OF AIRCRAFT OF THIS TYPE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L71 3O3  ONTTA4CH   E7SO                 
20060530001652006053000165GL  2006       5          30         2006FA0000535    120060518G7810DC00015B        EXHAUST RISER                           DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO                              ENGINE          CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW19107TX52                     C0310                                   ON A 100HR INSP NR 2 EX RISER CRACKED AT FLANGE. THIS HAS BEEN FOUND ON A NUMBER OF AIRCRAFT OF THIS TYPE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L71 3O3  ONTTA4CH   E7SO                 
20060530001662006053000166GL  2006       5          30         2006FA0000536    120060518G7810DC00015B        EXHAUST RISER                           DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO                              ENGINE          CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW19107TX52                     C0310                                   ON A 100HR INSP NR 2 EXHAUST RISER CRACKED AT FLANGE. THIS HAS BEEN FOUND ON A NUMBER OF AIRCRAFT OF THIS TYPE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L71 3O3  ONTTA4CH   E7SO                 
20060530001732006053000173CE  2006       5          30         2006FA0000537    120060520G5220                CHANNEL                                 CESSNA500   550         2076604CE                                                               ESC DOOR FRAME  DAMAGED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW1743SA                        0086                                    THE STRIKER PLATE HAD COME LOSE AT THE TOP LATCH POINT FOR THE ESCAPE HATCH ALLOWING THE LOCK PIN TO ELONGATE OUT THE HOLE. THIS REQUIRED THE REPLACEMENT OF 5511162-12 CHANNEL AND 5511162-48 ZEE CHANNEL.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L72 4F      A22CE                        
20060524002162006052400216SO  2006       5          24         2006FA0000538    220060510G8520                CAMSHAFT                                BEECH 58    58          1152740CE  CONT  O520  IO520CB     17032SO  HARTZLHCJ2Y BHCJ2YF2C   GL  ENGINE          WORN            D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW13866SH                       TH1083      298751R     DZ699           COMPRESSION CHECKED ENGINE, NR 2 CYLINDER 40/80.  REMOVED NR 2 CYL FOR REPAIR.  INSP INSIDE OF ENG, FOUND NR 1 CYL EXHAUST LIFTER/CAM LOBE BADLY WORN.  UNKNOWN HOW LONG IT HAS BEEN LIKE THIS, KNOW IT WOULD NOT HAVE LASTED TOO MUCH LONGER.  REBUILT/ZERO TIMED.  AIRPLANE SHOWN TO HAVE FLOWN AS LITTLE AS 5 HRS IN 9 MONTHS.  SUSPECT TOO LONG PERIOD BETWEEN ENGINE RUNS, LOSING OIL FILM ON LIFTER/LOBE CONTACT, MAYBE LITTLE CORROSION, CAUSING METAL /METAL WEAR AND (GALLING) BEARING SURFACES.  HAVE BEEN PULLING WAY TOO MANY CYLINDERS LATELY DUE TO LONG PERIODS OF STORAGE OF AIRCRAFT THAT WERE NOT PRESERVED FOR STORAGE.  (K)                                                                                                 1L72 3O3  O  3A16    E5CE    5  CP37EA    
20060524002172006052400217    2006       5          24         2006FA0000539    420060507G83007650004503074   BREATHER TUBE                           SKRSKYS76   S76B        8143007NE  PWA   PT6   PT6B36      52043EA                              ACCY GEARBOX    DETERIORATED    D      O   OTHER                                                                                           BJ SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION                                  CRCRUISE         1                      GL09176BA                       760317                                  ENROUTE TO A PICK UP A PATIENT.  WITHIN 4 MINUTES OF TAKEOFF, MEDICAL CREW REPORTED, SMELLED SMOKE IN CABIN, BECOMING VISIBLE ALSO.  PILOT NOTICED IT ABOUT SAME TIME.  PILOT RETURNED WITHOUT DELAY, APPROX 30 SECONDS BEFORE TOUCHDOWN, BAGGAGE COMPARTMENT SMOKE DETECTOR WENT OFF.  AC LANDED WITHOUT INCIDENT.  INVESTIGATION SHOWED NR 2 ENG ACCY GEARBOX VENT TUBE HAD BROKEN FREE OF ENG DECK FITTING.  THIS OVERBOARD BREATHER TUBE MADE OF A  VINYL MATERIAL, HAD DETERIORATED TO POINT OF BREAKING OFF OF FITTING ON BOTTOM OF ENG DECK.  TUBE RUNS THROUGH AFT CORNER OF BAGGAGE COMPT, WHEN TUBE BROKE, FILLED COMPT WITH OIL MIST/VAPOR THAT ILLUMINATED SMOKE DETECTOR.  VINYL TUBE WAS REPLACED, AC RETURNED TO SERVICE.  (K)   1G72 4U4  U  H1NE    E4EA                 
20060612002672006061200267NE  2006       6          12         2006FA0000540    120060508G26127630607902103   FIRE DETECTOR                           SKRSKYS76   S76B        8143007NE                                                               NR 1 ENGINE     FALSE ACTIVATIOND      O   OTHER                                                                                           N  FALSE WARNING                                                                 CRCRUISE         1                      GL09176BA                       760317                                  ENROUTE, WHEN NR 1 ENG FIRE WARNING SYS WAS ACTIVATED.  PILOT REPORTED WARNING LIGHTS, HORN AND T-HANDLES ILLUMINATED WITH FIRE WARNING INDICATION.  WARNING STAYED ON FOR 30 SECONDS, WENT OUT.  AFTER SHORT PERIORD OF TIME, WARNING CAME BACK.  PILOT DECLARED EMERGENCY WITH GRR CONTROLLERS.  WARNING WENT OUT AND CAME BACK ON 2 ADDITIONAL TIMES.  ENG PWR WAS REDUCED TO IDLE,THEN WAS SECURED USING FIRE T-HANDLE.  WHEN AC WAS IN SIGHT, IT WAS REPORTED, NO VISIBLE SMOKE TRAILING AC.  PILOT CONTINUED, MADE EMERGENCY LANDING W/O INCIDENT.  ENG WAS OPENED AND INSPECTED FOR ANY VISIBLE SIGNS OF DAMAGE.  NO FIRE INDICATIONS.  TROUBLESHOOTING RESULTED FROM DEFECTIVE FIRE WARNING SENSOR, REPLACED.  AC RETURNED TO SERVICE.  1G72 4U      H1NE                         
20060530001742006053000174SO  2006       5          30         2006FA0000541    120060523G32216705403         TRUNNION                                PIPER PA44  PA44180     7104402SO                                                               NLG             CRACKED         C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM038184U                       448095023                               NOSE LANDING GEAR TRUNNION CRACKED AT UPPER ATTACH POINTS AND LOWER DRAG LINK ATTACH POINT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L72 3O      A19S0                        
20060530001152006053000115    2006       5          30         2006FA0000542    420060515G2562AK450           ELT                                     CESSNA172   172L        2072432CE  LYC   O320  O320E2D     41508EA                              FUSELAGE        DEFECTIVE       D      K   NONE                                                                                            L  NO TEST                                                                       ININSP/MAINT     1                      SO149894G                       17259794                                BRAND NEW ELT UNIT AMERIKING AK-450 WAS INSTALLED ON THE AIRCRAFT 8/04. UNIT WORKED AFTER INSTALLATION WITH REMOTE PANEL, G-SWITCH AND TOGGLE SWITCH LOCATED ON THE UNIT AND AT SUBSEQUENT ANNUAL INSPECTION. AIRCRAFT HAS FLOWN APPROXIMATELY 25 HOURS SINCE INSTALLATION. ELT UNIT WAS FOUND DEFECTIVE DURING A ROUTINE INSPECTION ON 5/15/06. THE SIX D BATTERIES WERE FOUND TO BE AT FULL CHARGE, NO SIGNS OF CORROSION. UNIT SENT BACK TO AMERIKING IN CA. FOR WARRANTY REPAIR.                                                                                                                                                                                                                                                            1H71 3O3  ONT3A12    E274                 
20060614002082006061400208    2006       6          14         2006FA0000543    420060515G2562AK450           ELT                                     CESSNA172   172L        2072432CE  LYC   O320  O320E2D     41508EA                              FUSELAGE        DEFECTIVE       D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO149894G                       17259794                                BRAND NEW ELT UNIT WAS INSTALLED ON THE AIRCRAFT 8/04. UNIT WORKED AFTER INSTALLATION WITH REMOTE PANEL, G-SWITCH AND TOGGLE SWITCH LOCATED ON THE UNIT AND AT SUBSEQUENT ANNUAL INSPECTION. AIRCRAFT HAS FLOWN APPROXIMATELY 25 HOURS SINCE INSTALLATION. ELT UNIT WAS FOUND DEFECTIVE DURING A ROUTINE INSPECTION ON 5/15/06. THE 6 (D) BATTERIES WERE FOUND TO BE AT FULL CHARGE, NO SIGNS OF CORROSION. UNIT SENT BACK TO MFG FOR WARRANTY REPAIR.                                                                                                                                                                                                                                                                                          1H71 3O3  ONT3A12    E274                 
20060614002102006061400210GL  2006       6          14         2006FA0000544    220060526G8510                DRIVE GEAR                              AMTR  AVDFLYAVIDFLYER          GL  AMTR  430   CUYUNA430   19050GL                              ENGINE          DAMAGED         G      A   UNSCHED LANDING                                                                                 R  PARTIAL RPM/PWR LOSS                                                          CLCLIMB          1                      NM05157VM75                     0157                                    ACCIDENT INVESTIGATION.  ON CLIMB-OUT ENGINE RPM INCREASED AND PROPELLER RPM DECREASED. THE GRD-2000 GEAR REDUCTION UNIT WAS DISASSEMBLED AND THE DRIVE GEAR WAS FOUND TO DAMAGED.  (TEETH GONE)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1H71 3O3  I  EXPA1H71EXPE3I               
20060613001982006061300198EU  2006       6          13         2006FA0000545    120060511G2720                RUDDER PEDAL                            GROB  103TWNG103ATWINII 1660206EU                                                               COCKPIT         CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA014446T                       3824                                    SIGNIFICANT CORROSION NOTED AT HORIZONTAL BASE OF LEFT RUDDER PEDAL.  RUDDER PEDAL CRACKED AND STARTED TO DEFORM SLIGHTLY IN THE VICINITY OF THE CRACK.  THE RUDDER PEDAL IS PLATED AND THE CORROSION APPEARED TO HAVE STARTED FROM THE INSIDE BUT THE EXACT CAUSE HAS YET TO BE DETERMINED.  THESE PEDALS SHOULD BE EXAMINED AT LEAST EVERY YEAR DURING THE ANNUAL INSPECTION WITH A MIRROR AND LIGHT.                                                                                                                                                                                                                                                                                                                                         1K00 3O    0 G39EU                        
20060613002292006061300229GL  2006       6          13         2006FA0000546    120060526G2434657046          BRACKET                                 CIRRUSSR    SR20        05628AJGL  CONT  O360  IO360CONT   17025SO                              ENGINE          CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         UKUNKNOWN        1                      SO06145CD446                    1020                                    ALTERNATOR BRACKET FOUND CRACKED.  NEW PART IS OF A HEAVIER DESIGN BUT RETAINS THE SAME PART NUMBER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L71 3O3  ONTA00009CHE1CE                 
20060609002672006060900267SW  2006       6          9          2006FA0000547    120060602G781040B19822        EXHAUST RISER                           MOONEYM20   M20M        5870222SW  LYC   0540  TIO540AF1B  41532EA                              ENGINE          CRACKED         C      K   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      NM03223KT631                    270067                                  CUSTOMER SENT IN THE EXHAUST SYSTEM BECAUSE OF CRACKS FOUND IN THE WELDS OF THE RISER LEGS TO THE STACK TUBES OF THE NR 1 AND NR 2 SECTIONS.  ADVISED CUSTOMER TO REPLACE COMPONENTS. CUSTOMER BOUGHT NEW PARTS AND BROUGHT THEM IN TO HAVE ATTACHING PIECES INSTALLED TO CHECK ALIGNMENT.  THE CUSTOMERS REQUIREMENTS THAT THEY FIT UNIFORMLY.  GENERAL COMMENTS REGARDING THESE PARTS: THE WORKMANSHIP OF THE NEW PIECES WAS GENERALLY POOR IN MY OPINION, NOT REPRESENTATIVE OF THE TYPE OR QUALITY THAT SHOULD BE EXPECTED FROM A MAJOR AIRCRAFT ENGINE MANUFACTURER.   IF IMPROVEMENTS ARE NOT MADE TO THE COMPONENTS ON THIS ENGINE/AIRCRAFT MODEL, SIGNIFICANT SAFETY PROBLEMS SHOULD BE EXPECTED.                                       1L71 3O3  ORT2A3     E14EA                
20060612002332006061200233    2006       6          12         2006FA0000548    420060517G611305522311        BULKHEAD                                CESSNA172   172N        2072434CE  LYC   O320  O320*       41508EA                              SPINNER         CRACKED         B  WIWRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP07123GJ1100                   17270706                                DURING AN ANNUAL INSPECTION FO THE PROPELLER IT WAS NOTICED THAT THERE WERE CRACKS AROUND 3 OF THE BOLT HOLWS OD THE FORWARD SPINNER BULKHEAD.  THE PROBABLE CAUSE IS THAT THE BULKHEAD IS BEING STRESSED AND BENT AS IT IS BEING TIGHTENED AGAINST THE PROPELLER HUB.  IT IS SUGGESTED THAT THE SPINNER BULKHEAD BE MADE OF A THICKER MATERIAL.  (K)                                                                                                                                                                                                                                                                                                                                                                                           1H71 3O3  ONT3A12    E274                 
20060612002652006061200265CE  2006       6          12         2006FA0000549    120060516G27100510105365      CABLE                                   CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              RT AILERONS     FRAYED          B  WIWRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP07141CW2657                   172S9389                                DURING A 100 HOURS INSPECTION THE RT AILERON CROSSOVER CABLE WAS FOUND TO BE FRAYED AT THE PHANALIC BLOCK.  PROBABLE CAUSE IS FRICTION BETWEEN THE CABLE AND THE WARE BLOCK.  TO PREVENT RECURRENCE REMOVE PHANALIC BLOCK AND INCREASE TENSION ON CABLES.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H71 3O3  ONT3A12    1E10                 
20060609002492006060900249    2006       6          9          2006FA0000550    420060511G611305522311        BULKHEAD                                CESSNA172   172S        2072439CE  LYC   O360  IO360A1A    41514EA  MCAULY1A170 1A170E      GL  SPINNER         CRACKED         B  WIWRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP07533BM                       172S8340                                DURING 100 HRS INSPECTION, FOUND FORWARD SPINNER BULKHEAD CRACKED IN 2 PLACES AROUND PROPELLER BOLT HOLES.  RECOMMENDATION: DIMPLING OF BOLT HOLES.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1H71 3O3  ONT3A12    1E10    5  NP857     
20060612001572006061200157    2006       6          12         2006FA0000551    420060517G611305522311        BULKHEAD                                CESSNA172   172N        2072434CE  LYC   O320  O320*       41508EA  MCAULY1C160 1C160DTM    GL  SPINNER         CRACKED         B  WIWRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP07123GJ                       17270706                                DURING AN ANNUAL INSPECTION OF THE PROPELLER IT WAS NOTICED THAT THERE WERE CRACKS AROUND 3 OF THE BOLT HOLES OF THE FORWARD SPINNER BULKHEAD.  THE PROBLEM CAUSE IS THAT THE BULKHEAD IS BEING STRESSED AND BENT AS IT IS BEING TIGHTENED AGAINST THE PROPELLER HUB.  IT IS SUGGESTED THAT THE SPINNER BULKHEAD BE MADE OF A THICKER MATERIAL.  (K)                                                                                                                                                                                                                                                                                                                                                                                            1H71 3O3  ONT3A12    E274    5  NP910     
20060606002422006060600242SW  2006       6          6          2006FA0000552    120060513G6720500N72205       CABLE                                   HUGHES500N  500N        3027374SW                                                               ROTAT CONE CNTRLBROKEN          B  H2BRR   AUTOROTATION                                                                                    F  FLT CONT AFFECTED                                                             DEDESCENT        1                      WP05520HB                       LN029                                   PILOT WAS PRACTICING AUTOROTATION AND FELT A CHANGE IN THE PEDALS.  AFTER TOUCHDOWN, HE ATTEMPTED TO HOVER BY RAISING THE COLLECTIVE, AND THE HELICOPTER BEGAN TO SPIN, HE LOWERED THE COLLECTIVE, AND SHUTDOWN.  NO DAMAGE TO THE HELICOPTER WAS NOTED.  THE ROTATING CONE CONTROL CABLE WAS FOUND TO HAVE A CLEAN BREAK.  THE OTHER CABLES WERE INSPECTED AND FOUND OK.  PAN 500N72205 CABLE WAS INSPECTED AT THE LAST 300 HR INSPECTION AND WAS FOUND TO BE AIRWORTHY.  THIS PART IS NOT A LIFE LIMITED PART SO NO RECORD OF HRS IN SERVICE IS AVAILABLE.  RECOMMEND A SERVICE LIFE FOR THE CABLE: 1000 HRS.  (K)                                                                                                                            1G71 3U    NCH3WE                         
20060612001182006061200118    2006       6          12         2006FA0000554    120060523G8011ES6462382       STARTER                                                                                                                                 ENGINE          INOPERATIVE     B  WS9RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM07                                                                    STARTER IS DIFFICULT TO TURN.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        
20060612001602006061200160EA  2006       6          12         2006FA0000555    220060519G7320                CLIP                                    PIPER PA34  PA34200     7103405SO  LYC   O360  IO360A1A    41514EA                              ENGINE          MISSING         B  DYTRE   ENGINE SHUTDOWN                                                                                 O  OTHER                                                                         NRNOT REPORTED   1                      SO1515139                       347350025                               THE RETAINING CLIP FROM THE ROD END EITHER BROKE OR FELL OFF CAUSING THE THROTTLE CABLE TO DETACH FROM THE FUEL INJECTION SERVO.  THE ENGINE THEN WENT TO FULL POWER.  ENGINE HAD TO BE SHUT DOWN AND FEATHERED IN ORDER TO LAND THE AIRCRAFT.  RECOMMEND USING PN 452-606 BEARING INSTEAD WITH APPROPRIATE HARDWARE AND COTTER PIN.  (K)                                                                                                                                                                                                                                                                                                                                                                                                       1L72 3O3  O  A7SO    1E10                 
20060606002392006060600239NE  2006       6          6          2006FA0000556    120060512G2100S76A12          A/C PACK                                SKRSKYS76   S76A        8143006NE                                                               AC SYSTEM       BURNED          G  MV1RK   NONE                                                                                            B  SMOKE/FUMES/ODORS/SPARKS                                                      ININSP/MAINT     1                      EA1738   2749                   760087                                  AFTER THE DAYS FLIGHT, THE PILOT REPORTED THAT THE AIR CONDITIONING SYSTEM WAS INOPERATIVE.  MAINTENANCE WENT TO CHECK THE FREON CHANGE, WHEN THEY OPENED THE BAGGAGE AREA A FAINT SMELL OF BURNT WIRING WAS DETECTED.  UPON INSPECTION IT WAS FOUND THAT WIRE A1K925A1130AMP WAS BURNT THRU.  THE CURRENT LIMITER AND ITS MOUNT WERE HEAT DAMAGED.  THE RELAY K9 FOR THE AIR CONDITIONING SYSTEM ALSO LOOKS LIKE IT WAS EXPOSED TO HEAT.  THE DAMAGED PARTS WERE REMOVED, THE SYSTEM DEACTIVATED AND STOWED.  REP WAS CALLED AND IS COMING TO SEE WHAT WAS FOUND.  NO OTHER SYSTEMS ON BOARD THE AIRCRAFT ARE EFFECTED AND ALL DAMAGE CONFINED TO THE AIR-CONDITIONING SYSTEM.  (K)                                                            1G72 3U      H1NE                         
20060612001262006061200126    2006       6          12         2006FA0000557    120060517G8011MZ6222          STARTER                                                                                                                                 ENGINE          INOPERATIVE     B  WS9RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM07                                                                    WHINNING STARTER, WOULD NOT ENGAGE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  
20060612001582006061200158    2006       6          12         2006FA0000558    220060509G7314                DIAPHRAGM                                                                                                                               FUEL PUMP       WORN            B  YV4RK   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      SO05                                                                    DURING DISASSEMBLY FOR OVERHAUL, OVER THE PAST FEW MONTHS, HAVE NOTED THAT THE STEEL WASHER ON TOP OF THE DIAPHRAGM STEM IS LOOSE ON THE STEM AND IN SOME CASES IS PARTIALLY EATEN THROUGH OR WORN AWAY BY HAMMERING AGAINST UPSET END OF DIAPHRAGM STEM.  IF WASHER COMES COMPLETELY OFF, FUEL PUMP WILL BE INOPERABLE.  SOME WASHERS HAVE BEEN OBSERVED TO BE WORN 60-80 PERCENT THROUGH THEIR THICKNESS.  SB NR 548A IS APPLICABLE TO THIS ISSUE.  HOWEVER, MANY OF THE PUMPS WITH WORN/LOOSE WASHERS ARE OUTSIDE DATE CODES COVERED BY SB.  THIS HAS BEEN OBSERVED IN MODELS 15472 AND 15473.  AT THE SAME TIME, A MODEL 16775 WAS DISCOVERED TO HAVE A WORN/LOOSE WASHER.  THIS MODEL NR WAS NOT IN THE SB.  (K)                                                                     
20060609002512006060900251CE  2006       6          9          2006FA0000559    120060430G5346051313211       ATTACH BRACKET                          CESSNA175   175         2072502CE  LYC   O360  IO360A1A    41514EA  HARTZLHCC2Y HCC2YR1     GL  ENG MOUNT       CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL019366B                       55166                                   ENGINE MOUNT ATTACHMENT BRACKET BROKEN AND WITH CRACKS AT THE 12 AND 6 O`CLOCK POSITION.  CRACKS ON IB AND OB SIDES OF THE AN960-616 WASHER.  NORMAL FLIGHT CONDITIONS UNDER WHICH IT OCCURRED.  POSSIBLE CAUSE AN960-616 WASHER TOO SMALL.  LARGER AREA AND THICKER WASHER NEEDED TO SUPPORT THE UPPER LOAD.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O3  ONT3A17    1E10    5  CP920     
20060612001152006061200115CE  2006       6          12         2006FA0000560    120060430G5346051313211       ATTACH BRACKET                          CESSNA175   175         2072502CE  FRNKLN6AV3506A350C1     27043EA                              ENG MOUNT       BROKEN          D      K   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      AL01175FW                       55020                                   ENGINE MOUNT ATTACHMENT BRACKET BROKEN AND WITH CRACKS AT THE 12 AND 6 O`CLOCK POSITION.  CRACKS ON IB AND OB SIDES OF THE AN960-616 WASHER.  NORMAL FLIGHT CONDITIONS UNDER WHICH IT OCCURRED.  POSSIBLE CAUSE AN960-616 WASHER TOO SMALL.  LARGER AREA AND THICKER WASHER NEEDED TO SUPPORT THE UPPER ENGINE MOUNT LOAD.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                 1H71 3O3  ONT3A17    E9EA                 
20060612000592006061200059CE  2006       6          12         2006FA0000561    120060531G5346051313211       ATTACH BRACKET                          CESSNA175   175         2072502CE  CONT  IO360 IO360*      17025CE                              ENG MOUNT       CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      AL016622E                       56122                                   ENGINE MOUNT ATTACHMENT BRACKET WITH CRACKS AT THE 12 AND 6 O`CLOCK POSITION.  CRACKS ON IB AND OB SIDES OF THE AN960-616 WASHER.  NORMAL FLIGHT CONDITIONS UNDER WHICH IT OCCURRED.  POSSIBLE CAUSE AN960-616 WASHER TOO SMALL.  LARGER AREA AND THICKER WASHER NEEDED TO SUPPORT THE UPPER ENGINE MOUNT LOAD. (K)                                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3O3  ONT3A17    E1CE                 
20060609002522006060900252CE  2006       6          9          2006FA0000562    120060518G301040653481        BLANKET                                 LEAR  55    55LEAR      5170702CE  GARRTTTFE731TFE731*     01518WP                              STABILIZER      DAMAGED         B  FJKRK   NONE                                                                                            P  NO WARNING INDICATION                                                         CRCRUISE         1                      SO17417AM                       123                                     THIS INCIDENT HAPPENED IN FLIGHT.  CREW REPORTED THAT THERE WAS NO INDICATION IN COCKPIT, THAT THERE WAS A PROBLEM.  CREW DISCOVERED DAMAGE TO RT HORIZONTAL STAB ICE GUARD BLANKET DURING THERE POST FLIGHT INSPECTION.  IB SECTION OF THE RT ICE GUARD BLANKET WAS DAMAGED.  UPON FURTHER INVESTIGATION BY MECHANICS, WAS NOTED THAT A HOLE HAD BEEN MADE IN THE HORIZONTAL LEADING EDGE BY THE ARCING OF THE HORIZONTAL LEADING EDGE ICE GUARD BLANKET WIRING.  THE RT HORIZONTAL STAB LEADING EDGE AND ICE GUARD BLANKET WERE REPLACED.  (K)                                                                                                                                                                                                2L72 4F4  F  A10CE   E6WE                 
20060612001642006061200164EA  2006       6          12         2006FA0000563    120060424G2420728318          ADG                                     CNDAIRCL600 CL6001A11   1900302EA  LYC   ALF502ALF502*     41580EA                              NOSE BAY        DEPLOYED        G      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      SO05777GD                       1023                                    AIR DRIVEN GENERATOR (ADG) UNEXPECTED DEPLOYED ON POST TAKEOFF CLIMB OUT.  PRECAUTIONARY LANDING ACCOMPLISHED.  ADG MECHANICALLY RETRACTED/ SAFED; AIRCRAFT FERRIED TO MAINTENANCE DEPOT.  ALL WORK ACCOMPLISHED IAW MM.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  FRTA21EA   E6NE                 
20060607001352006060700135CE  2006       6          7          2006FA0000564    120060418G2820530010854       LINE                                    CESSNA340   340A        2076405CE                                                               CABIN           CORRODED        D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO09320RM5275                   340A0939                                DURING AC MAINT, A STRONG FUEL ODOR WAS OBSERVED IN CABIN OF THE AC.  THIS AC HAD SAT IDLE ON RAMP FOR AT LEAST 10 MONTHS.  EXTERIOR OF AC WAS INSPECTED FOR OBVIOUS FUEL LEAKS WITH NONE BEING DETECTED.  BY THIS TIME FUEL SMELL IN CABIN HAD CLEARED UP, AC ENGINES WERE OPERATED.  DURING PART OF THIS OPERATION, MECH WAS RUNNING ENGINES WITH FUEL SYS IN CROSSFEED POSITION, AGAIN NOTICED A STRONG FUEL ODOR.  AC WAS BROUGHT BACK TO HANGER, FLOOR PANELS WERE TAKEN UP IN AREA OF CROSSFEED LINES WHERE THEY RUN THROUGH CABIN AREA.  IT WAS OBSERVED THAT A HEATER DUCT THAT WAS RUNNING PERPENDICULAR TO CROSSFEED LINES AND WAS IN CONTACT WITH LINES HAD CAUSED CORROSION TO FORM AND RESULTED IN PINHOLES IN BOTH LINES.  (K)    1L72 3O      3A25                         
20060607001372006060700137CE  2006       6          7          2006FA0000566    120060524G5610991438011       WINDSHIELD                              CESSNA560   560XL       2076702CE  PWA   545   PW545A           NE                              COCKPIT         CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL13240B 3548                   5605057                                 PILOTS WINDSHIELD OUTER PANE CRACKED AT 39,000 FT.  IT IS BELIEVED THAT A HEATING ELEMENT SHORTED CAUSING THE OUTER PANE TO CRACK.  WINDSHIELD REMAINS STRUCTURALLY INTERGRAL WITH THE OUTER PANE CRACKED.  MFG ENGINEERING IS EVALUATING THE FAILURE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA22CE   E00059EN             
20060607001402006060700140EA  2006       6          7          2006FA0000567    220060601G7321                BEARING                                 BEECH 90    C90A        1152911CE  PWA   PT6   PT6*        52043EA                              FCU             FAILED          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05530CH2896                   LJ1322                                  THE BEARING IN FUEL CONTROL UNIT FAILED CAUSING THE LT ENGINE TO SURGE AND EXCEED THE N1, ITT AND TORQUE LIMITS.  THE ITT EXCEEDED 1000 C AND THE TORQUE EXCEEDED 1500 FT POUNDS FOR 5-10 SECONDS.  SHORTLY AFTER TAKEOFF, PILOTS REPORTED PLANE HAD YAWED TO THE RT AND FIRST CORRECTED FOR THE YAW BEFORE NOTICING ITT AND TORQUE ABOVE RED LINE.  PILOTS THEN REDUCED POWER AND RETURNED TO AIRPORT.  ENGINE WAS REMOVED FOR REPAIR AND ALL ROTATING PARTS WERE FOUND TO BE IN NEED OF REPLACEMENT.  IN-SITU TEST HAD BEEN DONE REGULARLY AND NO INDICATION OF BEARING INSPECTION BUT IT IS AT THE END OF THE NOTES UNDER THE FUEL SYSTEM INSPECTION.  BEARINGS ARE CALLED OUT FOR INSP/ REPLACEMT AT MID TBO OR 6 YEARS.                    1L72 3T3  TRT3A20    E2NE                 
20060612001992006061200199GL  2006       6          12         2006FA0000568    120060601G2720                SPRING                                  DIAMONDA40  DA40        2990002GL                                                               RUDDER          LOOSE           D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA23422DL                       42L002                                  THIS HAS TO DO WITH RUDDER CENTERING BUNGEES OR SPRINGS THERE IS ONE ON BOTH SIDES OF THE RUDDER.  AFTER FLT, MECHANIC NOTICED SOME PARTS SETTING ON RUDDER HORN AS IF THEY HAD BEEN REMOVED AND PUT THERE, AN INSP OF  RUDDER, IT WAS DETERMINED THAT THEY FELL OFF JUST AS AC WAS PARKED AS ALL OF PARTS FOR BUNGEE WAS THERE.  AFTER CONSULTING MAINT, PARTS ALONG WITH AC PARTS WERE REASSEMBLED USING LOCK TIGHT AS THERE IS NO LOCKING DEVICE.  PNS FOUND ON RUDDER ARE: (ROD, D60-2723-00-31) (SPACER, D60-2723-00-32) (SPRING, VD-283A-10) (SPACER, D60-2723-00-33) IF THESE PARTS WOULD HAVE FALLEN OUT IN FLIGHT THIS COULD HAVE LOCKED UP THE RUDDER. SUGGEST THERE SHOULD BE SOME SORT OF LOCKING DEVICE INSTALLED.  (K)            1L71 3O    NTA47CE                        
20060613001972006061300197NE  2006       6          13         2006FA0000569    220060606G74146351            SCREW                                   MAULE MT7235MT7235      5470209SO  LYC   O540  IO540W1A5   41532NE                              MAGNETO         LOOSE           D      K   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      SW01116CP394  394               18063C                                  CHECKED TIMING BOTH WERE OUT OF TIME.  REMOVED BOTH MAGS, THE PIVOT SCREW WAS LOOSE.  REPLACED POINTS & CAP, WITH 500 HR INSP.  BOTH MAGS WERE INSTALLED NEW IN 04/2002 AT 46.1 TT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3O3  ONC3A23    1E4                  
20060612001162006061200116SO  2006       6          12         2006FA0000571    120060531G740010382585        POINTS                                  PIPER PA34  PA34220T    7103420SO  CONT  O360  TSIO360KB   17025SO                              ENGINE          FAILED          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE038456H9                      348233011   268216R                     THE POINTS WHICH ONLY HAD A TOTAL OF 9.3 HR, HAD THE PLASTIC PORTION WHICH RIDES THE CAM, MELT ON THE METAL OF THE POINTS WHICH REDUCED THE GAP TO CAUSE MISFIREING.  CAPACITOR CHECKED GOOD AND WAS NOT REPLACED ON THE 500 HR INSP.  AFTER A NEW POINT SET WERE INSTALLED CHANGED THE CAPACITOR.  NOTE:  WIRE BROKE ON OLD CAPACITOR.  (K)                                                                                                                                                                                                                                                                                                                                                                                                    1L72 3O3  O  A7SO    E9CE                 
20060612001142006061200114SW  2006       6          12         2006FA0000572    120060519G3210AN3H11A         BOLT                                    GULSTM690TP 695A        7630519SW  GARRTTTPE331TPE33110    01514WP                              NLG STEERING ACTSHEARED         B  O9IRO   OTHER                                                                                           J  WARNING INDICATION                                                            APAPPROACH       1                      NM09333UP3934                   96015                                   DURING LANDING GEAR EXTENSION ON APPROACH, (GEAR IN TRANSIT) LIGHT REMAINED ON, NLG DID NOT INDICATE DOWN AND LOCKED.  INITIAL FLY BYS INDICATED NLG TO BE ONLY PARTIALLY EXTENDED.  AFTER RECYCLING GEAR SEVERAL TIMES, CLUNK WAS HEARD, NLG EXTENDED.  INSP REVEALED 4 (AN3) BOLTS USED TO SECURE HYD STEERING ACTUATOR TO NLG OLEO STRUT, SHEARED RESULTING IN STEERING ACTUATOR HANGING ONLY BY ITS HYD LINES.  UNSECURED STEERING ACTUATOR HAD POSSIBLY JAMMED PREVENTING FULL EXTENSION OF NLG.  RADOME DAMAGE WAS EVIDENT, NO OTHER DAMAGE HAS BEEN FOUND.  4 BROKEN BOLTS CAN BE DAMAGED BY EXCEEDING NLG TURN LIMITS DURING TOWING.  BOLTS WERE WEAKENED BY EXCESSIVE TURNING WHILE TOWING. SOMETIME IN PAST, FAILED DURING FLIGHT. (K)1H72 4T4  T  2A4     E4WE                 
20060612001222006061200122CE  2006       6          12         2006FA0000573    120060525G5541053100121       RIB             CESSNA                  CESSNA172   172         2072402CE  CONT  O300  O300A       17022SO                              RUDDER          CRACKED         H  ET9TO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM075039A5752                   28039       10851D5B                    RIB, CRACKED AT VERTICAL HINGE LINE JUNCTURE.  STRESS FROM COUNTER WEIGHT AND NORMAL WEAR.  AGE OF THE PART AND THE WIND.  SUBMITTER RECOMMENDS CLOSE INSPECTION AND REPLACEMENT OF PART IF DAMAGED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3O3  ONT3A12    E253                 
20060612001302006061200130GL  2006       6          12         2006FA0000574    120060531G7810                FLANGE          DIAMON                  DIAMONDA40  DA40        2990002GL  LYC   O360  IO360A1A    41514EA  HARTZLHCC2Y HCC2YR1     GL  EXHAUST RISER   BROKEN          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM05431JP82         1PA520014   40431       L31683351A  CH338383B       FOUND NR 2 CYLINDER EXHAUST RISER FLANGE BROKEN.  DISCOVERED WHEN DISASSEMBLY EXHAUST FOR MODIFICATION IAW MSB-4000411.  PROBABLE CAUSE OF BREAKING FROM EXCESS VIBRATION.  RECOMMEND INSTALLING MSB-40-004/1 MUFFLER BRACE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L71 3O3  ONTA47CE   1E10    5  CP920     
20060612001742006061200174EU  2006       6          12         2006FA0000575    120060309G7600L810BQ54        SOLENOID                                SNIAS 350   AS350B3     8680954EU  TMECA ARRIELARRIEL2B         NE                              AUTOTHROTTLE    INOPERATIVE     D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA01187AE673                    3846        22469                       PROLONGED OPERATION IN MANUAL MODE CAN CAUSE SOLENOID OVERHEATING AND PISTON SEIZURE.  FAILURE OF THE PISTON MOVEMENT MAY RESULT IN THE PILOT BEING UNABLE TO APPLY ADDITIONAL MANUAL THROTTLE BEYOND THE VOL (GATE).  THIS CAN RESULT IN ROTOR RPM DECAY IN CERTAIN CRITICAL SITUATIONS.  WHILE PERFORMING MAINTENANCE OF COLLECTIVE TWIST GRIP THROTTLE AUTO/MAN SOLENOID PISTON, SYSTEM WAS ACTIVATED FOR 10 MIN.  FOLLOWING A 30 SECOND TIME IN WHICH SOLENOID WAS RELAXED PWR WAS AGAIN APPLIED.  PISTON FAIL TO FULLY SEAT IN THE SOLENOID.  PART WILL BE REPLACED. CMD AS350-06-15 RESCINDED AND REPLACED BY CMD AS350-06-16.  NEW CMD CHANGES RELAXED TIME FROM 30 SEC TO 15 MIN TO ALLOW THE SOLENOID TO COOL BEFORE REACTIVATION.  (K)1G71 3U3  U  H9EU    E00054EN             
20060614002292006061400229SO  2006       6          14         2006FA0000576    220060606G8520                NUT                                     CIRRUSSR    SR22        2130001GL  CONT  O550  IO550*           SO                              NR 4 CYLINDER   SPLIT           D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL15746C 699                    0413        686383                      THRU STUD NUT SPLIT ON NR 4 CYLINDER TOP THRU STUD.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L71 3O3  ONTA00009CHE3SO                 
20060614002192006061400219SW  2006       6          14         2006FA0000577    120060521G28412731            GAUGE                                   BBAVIA7     7CCM        21101MWSW  CONT  C90   C90*        17009SO                              COCKPIT         STUCK           G      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL134629E                       7CCM196                                 AIRCRAFT LOST POWER AND LANDED IN A HAYFIELD UP ON ITS NOSE.  PILOT STATED HE CHECKED THE FUEL GAUGE PRIOR TO THE FLIGHT AND IT READ (HALF FULL).  HE DID NOT VISUALLY CHECK THE QUANTITY.  INVESTIGATION REVEALED FUEL TANK TO BE EMPTY AND GAUGE STUCK IN THE (HALF FULL) POSITION.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                      1H71 3O3  O  A759    E252                 
20060614002272006061400227EA  2006       6          14         2006FA0000579    120060420G5310                DOOR FRAME                              DHAV  DHC3  DHC3        2800202EA                                                               FUSELAGE        CORRODED        D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL05435B 12295                  183                                     FORWARD FUSELAGE STRUTS (DOOR POSTS) CORRODED THROUGH FROM INSIDE OUT.  THIS IS THE SAME DESIGN AS THE DOOR POST THAT ARE REQUIRED BY AD TO BE REPLACED EVERY 15 YEARS OR INSPECTED ANNUALLY BY ULTRASOUND.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1H71 3R      A815                         
20060614002232006061400223SO  2006       6          14         2006FA0000580    220060508G8520                CONNECTING ROD                          BEECH 58    58          1152740CE  CONT  O550  IO550*           SO  HARTZLHCJ3Y PHCJ3YF1    GL  LT ENGINE       UNKNOWN         D      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CRCRUISE         1                      SW11106GA                       TH437       8244276R    ED3372          50 MILES OUT OF HOME BASE, PILOT HEARD A (POP) CAME FROM LEFT ENGINE,  THEN NOTICED OIL PRESSURE START THE FALL.  FEATHERED PROP AND SECURED ENGINE.  MADE A UNEVENTFUL LANDING.  INSP FOUND NR 4 CYLINDER ON L/E DDEPARTED FROM ENGINE AND NR 4 ROD BROKEN.  SUSPECT EITHER ROD BOLTS FAILED OR IMPROPERLY TORQUED, OR CYLINDER  IMPROPERLY TORQUED.  ENGINE COMPLETE LOSS.  (K)                                                                                                                                                                                                                                                                                                                                                               1L72 3O3  O  3A16    E3SO    5  CP36EA    
20060614002132006061400213    2006       6          14         2006FA0000581    420060504G611305503214        BULKHEAD                                CESSNA172   172M        2072418CE                                                               PROP SPINNER    CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM019379H445                    17266128                                DURING ROUTINE SCHEDULED PHASE INSPECTION.  FOUND FORWARD PROP SPINNER BULKHEAD CRACKED RADIALLY OUTWARD FROM MOUNTING BOLT HOLES NEXT TO BEND RADIUS.  PROPELLER MOUNTING BOLT BOLT TORQUE AND INDEXING FOUND CORRECT.  SUSPECT EITHER IMPROPER HEAT TREAT DURING MFG, OR POSSIBLY TOO TIGHT OF BEND RADIUS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O    NT3A12                         
20060614002162006061400216SO  2006       6          14         2006FA0000582    120060522G3211401421          BOLT                                    PIPER PA34  PA34200T    7103406SO  CONT  O360  TSIO360*    17025SO                              NLG             LOOSE           D      K   NONE                                                                                            O  OTHER                                                                         LDLANDING        1                      NM137609C                       347670097                               NOSE GEAR RETRACTED ON LANDING.  FOUND BOLT PN 401-421 (AN6-41A) LOOSE WHERE NOSE GEAR MOUNT BOLTS TO BULKHEAD AT STA 49.5.  THIS RELEAVED DOWNLOCK LINK OVER CENTER POSITION.  BOLTS SHOULD BE CHECKED EACH 500 HRS. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 3O3  O  A7SO    E9CE                 
20060621002342006062100234CE  2006       6          21         2006FA0000584    120060602G554396630000335     TRIM TAB                                BEECH 90    C90         1152913CE  PWA   PT6   PT6A11      52043NE                              RUDDER TRIM     MISMANUFACTURED D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE07690GT164        LJ1728      LJ1727                                  WHEN INSPECTED IAW SB, THIS AC WAS IDENTIFIED AS MISSING THE DRAIN PROVISIONS.  C/A WAS TAKEN IAW SB.  DURING OUR RESEARCH INTO THIS MATTER IT WAS IDENTIFIED THAT THE CCORRELATING AD TO THIS ISSUE.  THIS IS A NEARLY NEW AC.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L72 3T3  T  3A20    E4EA                 
20060621002362006062100236CE  2006       6          21         2006FA0000585    120060518G2434991059111RX     ALTERNATOR                              CESSNA172   172S        2072439CE  LYC   O360  IO360A1A    41514EA                              ENGINE          SHORTED         B  NF2RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL03140JA                       172S8653                                ALTERNATOR WENT SEVERE OVER VOLT DUE TO INTERNAL SHORT IN THE FIELD WINDINGS.  SHORT FRYED THE ACU AND BOSS 1 DIODE (AVIONICS BUSS) DUE TO BADLY DAMAGED ACU, ACU COULD NOT GET ALTERNATOR OFF LINE.  DUE TO BOSS 2 DIODE FAILURE AVIONICS BUSS WAS HOT WITH AVIONICS MASTER OFF OVER VOLT BURNED UP ALL RADIOS.  ALL ENGINE GAUGES, FUEL GAUGES ANNUNICATOR PANEL AND FLASHING BEACON.  THIS IS THE 5TH ALTERNATOR WITH MAJOR PROBLEMS IN THE PAST 11 MONTHS.  (K)                                                                                                                                                                                                                                                                             1H71 3O3  ONT3A12    1E10                 
20060621002622006062100262CE  2006       6          21         2006FA0000586    120060518G2435230790001       STARTER GEN                             BEECH 100   B100        1152919CE  GARRTTTPE331TPE3316     01514WP                                              SEIZED          B  R4ORO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO33301TS                       BE76        P271610                     RT ENGINE WOULD NOT START.  TROUBLESHOT AND FOUND RT STARTER GENERATOR SEIZED DUE TO BRUSHES WORN BEYOND LIMITS AND PIGTAILS ARCHING TO ARMATURE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L72 4T4  T  A14CE   E4WE                 
20060621002322006062100232EU  2006       6          21         2006FA0000587    120060202G3213TB2047007       CYLINDER                                SOCATATB20  TB20TRINIDAD8680695EU  LYC   O540  IO540*      41532EA                              LT MLG          UNSERVICEABLE   D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM092808W800                    1083                                    MLG HYD CYL, PN TB2047007/SN WO300497 WAS REMOVED AND SENT FOR INTERNAL LEAK AND A VERY STIFF SPOT ABOUT CENTER OF TRAVEL.  CYL WAS RETURNED, REPAIRED, WARRANTY AS IS.  INSTALL CYL ON LT MLG.  INTERNAL LEAK NO LONGER EXISTED.  UPON TESTING EMERGENCY EXTENSION CYL WOULD NOT ALLOW LT MAIN TO EXTEND, STIFF SPOT CENTER OF TRAVEL,  CAUSE: REPAIR STATION STAMPED TAG, DISTORTING CYLINDER? CYLINDER HAS TO BE REPLACED WITH SERVICEABLE UNIT.  (K)                                                                                                                                                                                                                                                                                        1L71 3O3  ORTA51EU   1E4                  
20060621002382006062100238NM  2006       6          21         2006FA0000588    120060607G2910                CAP                                     BOEING737   737205      1384456NM  PWA   JT8   JT8D17A     52049NE                              CHECK VALVE     INOPERATIVE     C  NACRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03736BP           0448        23465                                   AFTER COMPLETING 2 FLIGHTS, (A) HYDRAULIC SYSTEM BECAME INOPERATIVE.  A LARGE AMOUNT OF FLUID WAS NOTED ON THE GROUND UNDER THE LT WHEEL.  UPON FURTHER INVESTIGATION IT WAS NOTED THAT THE RT (A) SYSTEM MODULE CHECK VALVE INSTALLATION CAP HAD SHEARED IN THE MODULE CHECK VALVE INSTALLATION CAP HAD SHEARED IN THE MODULE PACKAGE, ALLOWING A LARGE QUANTITY OF HYDRAULIC FLUID TO BE LOST.  DO NOT HAVE A PROBABLE CAUSE OR ANY RECOMMENDATIONS.  (K)                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA16WE   E2EA                 
20060621002502006062100250    2006       6          21         2006FA0000589    420060412G2562                BATTERY                                 CNDAIRCL600 CL6001A11   1900302EA                                                               ELT             LEAKING         C  PAIRK   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      EA01673TS           WO62231     1073                                    A STRONG ACIDIC ODOR WAS PRESENT AFTER REMOVING ELT BATTERY FROM ELT INSPECTION FOUND A THICK WHITE LIQUID ON THE NEGATIVE SIDE OF ONE BATTERY CELL.  THE EXPIRATION DATE OF THE ELT BATTERY IS APRIL 2010 (4 MORE YEARS).  THE ELT BATTERY OUTPUT IS 13.2 VOLTS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA21EA                        
20060627003112006062700311CE  2006       6          27         2006FA0000590    120060608G2810714145          VENT LINE                               BBAVIA8     8KCAB       2110612CE  LYC   O360  AEIO360*         EA                              FUEL CELL       CRACKED         B      K   NONE                                                                                            KB FLUID LOSS                SMOKE/FUMES/ODORS/SPARKS                            ININSP/MAINT     1                      GL21316CA152  152               10132006    L3247851A                   CREW REPORTED STRONG SMELL OF FUEL IN CABIN.  MX INSPECTED FOUND FUEL LEAKING ONTO CARPET ON THE FWD LT SIDE OF CABIN. TRACED LEAK TO THE VENT LINE HEADER TANK ATTACH FITTING.  FITTING FOUND TO BE TIGHT BUT LINE CRACKED AT COMPRESSION SLEEVE CONNECTOR. LINE AND CONNECTOR REPLACED NO LEAKS NOTED.                                                                                                                                                                                                                                                                                                                                                                                                                                        1H71 3O3  O  A21CE   1E10                 
20060619001892006061900189CE  2006       6          19         2006FA0000591    120060608G2810714145          SLEEVE                                  BBAVIA8     8KCAB       2110612CE  LYC   O360  AEIO360*         EA                              FUEL LINE       BROKEN          B      O   OTHER                                                                                           KB FLUID LOSS                SMOKE/FUMES/ODORS/SPARKS                            NRNOT REPORTED   1                      GL21316CA152  152               10132006    L3247851A                   CREW REPORTED STRONG ODOR OF FUEL IN CABIN.MX INSPECTED FOUND FUEL LEAKING ONTO CARPET ON THE FWD LEFT SIDE OF CABIN. TRACED LEAK TO THE VENT LINE HEADER TANK ATTACH FITTING. FITTING FOUND TO BE TIGHT BUT LINE CRACKED AT COMPRESSION SLEEVE CONNECTOR. LINE AND CONNECTOR REPLACED NO LEAKS NOTED.                                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3O3  O  A21CE   1E10                 
20060621002612006062100261    2006       6          21         2006FA0000592    420060605G61130522311         BULKHEAD                                CESSNA172   172S        2072439CE  LYC   O360  IO360A1A    41514EA                              SPINNER         CRACKED         B  WIWRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP07787WW100                    172S8589                                DURING A 100 HOUR INSPECTION FO THE PROPELLER IT WAS NOTICED THAT THE FORWARD SPINNER BULKHEAD HAD CRACKS AROUND ALL 6 BOLT HOLES.  THE PROBABLE CAUSE IS DURING THE TORQUING PROCESS THE BULKHEAD IS BEING STRESSED AND BENT AS IT IS PULLED TIGHT TO THE PROP HUB.  IT IS SUGGESTED THAT THE SPINNER BULKHEAD BE MADE OF THICKER MATERIAL.  (K)                                                                                                                                                                                                                                                                                                                                                                                               1H71 3O3  ONT3A12    1E10                 
20060621002092006062100209CE  2006       6          21         2006FA0000593    120060606G324012806160        LINE                                    CESSNA206   T206H       2073303CE  LYC   O540  TIO540*     41532EA                              RT MLG BRAKE    LEAKING         B  WIWRO   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      WP072147Q117                    T20608420                               DURING NORMAL OPERATION RT BRAKE STARTED LEAKING.  REMOVED WHEEL FAIRING AND FOUND A SCREW FROM THE FAIRING CHAFING INTO THE LOWER BRAKE LINE CAUSING THE LINE TO LEAK AND ALMOST FAIL, THEREFORE IT IS RECOMMENDED THAT PROPER ROUTING IS ASSURED DURING INSPECTIONS AND THIS AREA IS ROUTINELY INSPECTED FOR LEAKS AT EVERY PREFLIGHT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3O3  ORTA4CE    E14EA                
20060621000312006062100031NE  2006       6          21         2006FA0000594    220060427G72500292208230      MANIFOLD                                SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1     60030NE                              GAS GEN         COKED           B  GO4DK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP13711JH2551                   3397        7022                        DURING A 500 HR (T-INSPECTION), COULD NOT SPIN COMPRESSOR DISK, DUE TO GAS GENERATOR INJECTION MANIFOLD COKING.  MFG TECH REMOVED AND REPLACED INJECTION MANIFOLD ON MODULE NR 3.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1G71 3U3  U  H9EU    E19EU                
20060621002542006062100254SW  2006       6          21         2006FA0000595    120060602G57115271L           SPAR                                    BBAVIA7     7ECA        21101NNSW  LYC   O235  O235C1      41505EA                              LT WING         CRACKED         B  YEBRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE059562S2573                   84          RL338815                    REQUIRED INSPECTION OF WOODEN WING SPARS IN ACCORDANCE WITH AD.  REVEALED A COMPRESSION CRACK IN THE LT WING FWD SPAR AT THE TOP OB OF WING STRUT ATTACH DOUBLER PLATE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H71 3O3  O  A759    E223                 
20060621002452006062100245CE  2006       6          21         2006FA0000596    120060607G32336632201000005   ACTUATOR                                LEAR  45    45LEAR      5170805CE                                                               NLG             LEAKING         B  B08RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW05CFBLJ                       45270                                   DURING MAINTENANCE, TECH DISCOVERED LEAKING NLG ACTUATOR.  FACILITY GAINED ACCESS, REMOVED AND REINSTALLED THE ACTUATOR WITH A REPAIRED UNIT AND RETURNED THE AC TO SERVIC.  DURING ATTEMPT TO BEGAN NORMAL TOWING OPERATIONS TO POSITION THE AIRCRAFT FOR DEPARTURE, NLG BEGAN TO RETRACT.  IMMEDIATELY CEASED THE TOWING OPERATION AND WERE ABLE TO PLACE A JACK UNDERNEATH THE AIRCRAFT TO SUPPORT IT AND PREVENT ANY DAMAGE.  WITH LANDING GEAR FULLY EXTENDED AN INTEGRAL MECHANISM HOLDS THE ACTUATOR DOWN AND LOCKED UNTIL HYDRAULIC PRESSURE IS APPLIED.  SUSPECT FAILURE OF INTEGRAL LOCKING MECHANISM.  (K)                                                                                                                           2L72 4F    RTT00008WI                     
20060621002572006062100257CE  2006       6          21         2006FA0000597    120060613G7120051313211       GUSSET                                  CESSNA175   175         2072502CE  CONT  O300  GO300*      17022SO                              ENGINE MOUNT    CRACKED         B  QI2RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL156540E2043                   56040                                   FOUND 2 OF 4 ENGINE MOUNT TO FIREWALL BRACKETS CRACKED, BRACELETS ARE LOCATED IN CABIN, ATTACHING AC SKIN TO FIREWALL.  POSSIBLE CAUSE OF CRACKING MAY BE OVERTORQUING OF ENGINE MOUNT TO FIREWALL BOLTS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H71 3O3  ONT3A17    E298                 
20060621002432006062100243CE  2006       6          21         2006FA0000598    120060613G7120051313210       GUSSET                                  CESSNA175   175         2072502CE  CONT  O300  GO300*      17022SO                              ENGINE MOUNT    CRACKED         B  QI2RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL156540E2043                   56040                                   FOUND 2 OF 4 ENGINE MOUNT TO FIREWALL BRACKETS CRACKED, BRACKETS ARE LOCATED IN CABIN, ATTACHING AC SKIN TO FIREWALL.  POSSIBLE CAUSE OF CRACKING MAY BE OVERTORQUING OF ENGINE MOUNT TO FIREWALL BOLTS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3O3  ONT3A17    E298                 
20060621002252006062100225CE  2006       6          21         2006FA0000599    120060613G712005131329        GUSSET                                  CESSNA175   175         2072502CE  CONT  O300  GO300*      17022SO                              ENGINE MOUNT    CRACKED         B  QI2RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL156540E2043                   56040                                   FOUND 2 OF 4 ENGINE MOUNT TO FIREWALL BRACKETS CRACKED.  BRACKETS ARE LOCATED IN CABIN, ATTACHING AC SKIN TO FIREWALL.  POSSIBLE CAUSE OF CRACKEING MAY BE OVERTORQUING OF ENGINE MOUNT TO FIREWALL BOLTS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1H71 3O3  ONT3A17    E298                 
20060621002482006062100248SO  2006       6          21         2006FA0000600    120060609G551163460000        SPAR                                    PIPER PA28  PA28180     7102808SO  LYC   O360  O360*       41514EA                              STABILATOR      CORRODED        B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP118402W2360                   282616                                  WHILE OPENING SOME SKIN LAPS TO TREAT SURFACE CORROSION THE LT SIDE OF THE MAIN SPAR ABOUT 2.5 FEET FROM TIP WAS FOUND TO HAVE SEVERE INTERGRANULAR CORROSION TO THE POINT WHERE A 4-5 INCH LONGITUDNAL CRACK ABOUT .2500 INCH WIDE WAS FOUND.  PART WAS SCRAPPED AND REPLACED WITH NEW ASSY, TREATED AC WITH ACF50.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                       1L71 3O3  O  2A13    E286                 
20060621002592006062100259CE  2006       6          21         2006FA0000601    120060601G2450251005          FUSE                                    BEECH MU300 400A        1155402CE                                                               EMER BUSS       FAILED          B  E81RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL03787TA                       RK260                                   FLIGHT CREW REPORTED NO BATTERY VOLTAGE INDICATION ON VOLTMETER WITH ALL DC BUSSES POWERED.  TROUBLESHOOTING FOUND AIRCRAFT WOULD NOT GO INTO EMERGENCY POWER OR PERFORMED FEEDER FAULT TEST.  FOUND 5A MICROFUSE F105 CONNECTED TO K005 EMERGENCY BUSS POWER RELAY OPEN.  REPLACED F105 FUSE, ALL DC POWER FUNCTIONS NORMAL, NO FAULTS NOTED.  (K)                                                                                                                                                                                                                                                                                                                                                                                             2H72 4F    RTA16SW                        
20060621002522006062100252    2006       6          21         2006FA0000602    420060530G22136227410302      CIRCUIT CARD                            BEECH MU300 400A        1155402CE                                                               FCC             INTERMITTENT    B  E81RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL03408CW                       RK108                                   FLIGHT CREW REPORTED AUTOPILOT PITCH TRIM FAILURE ANNUNCIATION CAME ON DURING CLIMB WITH AUTO PILOT DISCONNECTED.  AIRCRAFT REPPORTED TO HAVE PITCH-UP MOVEMENT.  FOUND NR 1 FCC-850 CARD INTERMITTENTLY NOT CROSS-TALKING TO NR 2 FCC-850 CARD.  REPLACED NR 1 FCC 850 CARD WITH OVERHAULED UNIT.  GROUND/FLIGHT CHECKS SATISFACTORY.  (K)                                                                                                                                                                                                                                                                                                                                                                                                     2H72 4F    RTA16SW                        
20060621002312006062100231    2006       6          21         2006FA0000603    420060530G22136226717004      SERVO                                   BEECH MU300 400A        1155402CE                                                               YAW DAMPER      INTERMITTENT    B  E81RO   OTHER                                                                                           J  WARNING INDICATION                                                            APAPPROACH       1                      GL03408CW                       RK108                                   FLIGHT CREW REPORTED PILOTS CONTROL WHEEL TRIM INTERRUPT/AUTOPILOT DISENGAGE SWITCH NOT DISCONNECTING YAW DAMPER ON FINAL APPROACH.  FOUND CONTROL WHEEL SWITCH OPERATIONS NORMAL.  REPLACED SVO-85C YAW DAMPER SERVO WITH OVERHAULED UNIT.  ALSO, REPLACED NR 1 FCC-850 CARD WITH OVERHAULED UNIT TO CORRECT ADDITIONAL AUTOPILOT INTERMITTENT PITCH TRIM FAILURE FAULT.  GROUND AND FLIGHT TESTS SATISFACTORY.  (K)                                                                                                                                                                                                                                                                                                                           2H72 4F    RTA16SW                        
20060621002562006062100256SO  2006       6          21         2006FA0000604    120060614G273062701159        CONTROL CABLE                           PIPER PA32  PA32RT300   7103215SO  LYC   0540  IO540K1G5D  41532SO  HARTZLHCC3Y HCC3Y*      GL  ELEVATORS       SEPARATED       D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO11317092741                   32R7885121  L1571048A   DY4524A         CABLE TURNBUCKLE MALE END SEPARATED AT FITTING DURING ROLLOUT AFTER LANDING.  FITTING SEEMS TO HAVE CORRODED FROM THE SHANK CORE AND PROGRESSED OUTWARD TO THE SURFACE OVER TIME.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L71 3O3  O  A3SO    1E4     5  CP25EA    
20060711001062006071100106    2006       7          11         2006FA0000605    420060621G3460                DISPLAY                                                                                                                                 COCKPIT         MALFUNCTIONED   C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL07                                                                    TO DATE, HAVE EXPERIENCED 12 SEPARATE FAILURES OF THE MULTIFUNCTION DISPLAYS (MFD) WITH 6 OF THE 7 AIRCRAFT. THESE FAILURES HAVE OCCURRED EITHER IN FLIGHT OR ON THE GROUND. THERE IS NO APPARENT PATTERN OR FOREWARNING RELATED TO THESE FAILURES.  THESE FAILURES CAUSE AN UNAIRWORTHY CONDITION OF THE AIRCRAFT DUE TO THE LACK OF OIL TEMPERATURE INDICATION. ALSO, ACCORDING TO THE PA 28-161 MFG POH, SECTION 9, SUPPLEMENT 10, SECTION 2, PARAGRAPH B TITLED "MFD LIMITATIONS", ITEM 4, (AIRCRAFT DISPATCH IS PROHIBITED WHEN THE MFD IS INOPERATIVE.)  CURRENTLY, MANUFACTURERS ARE INVESTIGATING THIS PROBLEM, BUT NO RESOLUTION HAS BEEN FOUND.                                                                                                                                 
20060627003122006062700312CE  2006       6          27         2006FA0000606    120060622G5730                SKIN                                    CESSNA402   402B        207590PCE                                                               LT WING         CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO156375X5321                   402B1338                                DURING AN ANNUAL INSPECTION, A CRACK WAS FOUND ON THE LT WING SKIN AT THE OB AILERON ATTACH POINT, WHICH IS ALSO THE MAIN FUEL TANK AFT ATTACH POINT. UPON FURTHER INSPECTION OF AREA, THE RIVETS THAT ATTACH THE AILERON SUPPORT TO THE REAR SPAR WERE FOUND SHEARED, CAUSING THE MAIN FUEL TANK TO HAVE MOVEMENT.  IF LEFT UNDETECTED, COULD CAUSE MAIN FUEL TANK STRESS AT THE FORWARD ATTACH POINTS, CRACKED REAR SPAR OR POSSIBLE SEPARATION OF TANK. THIS IS THE SECOND AIRCRAFT THAT THIS PROBLEM WAS FOUND ON.                                                                                                                                                                                                                          1L72 3O      A7CE                         
20060627003132006062700313CE  2006       6          27         2006FA0000607    120060622G5730                SKIN                                    CESSNA402   402B        207590PCE                                                               LT WING         CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO156375X5321                   402B1338                                DURING AN ANNUAL INSPECTION, A CRACK WAS FOUND ON THE LT WING SKIN AT THE OB AILERON ATTACH POINT, WHICH IS ALSO THE MAIN FUEL TANK AFT ATTACH POINT. UPON FURTHER INSPECTION OF AREA, THE RIVETS THAT ATTACH THE AILERON SUPPORT TO THE REAR SPAR WERE FOUND SHEARED, CAUSING THE MAIN FUEL TANK TO HAVE MOVEMENT. IF LEFT UNDETECTED, COULD CAUSE MAIN FUEL TANK STRESS AT THE FORWARD ATTACH POINTS, CRACKED REAR SPAR OR POSSIBLE SEPARATION OF TANK. THIS IS THE SECOND AIRCRAFT THAT THIS PROBLEM WAS FOUND ON.                                                                                                                                                                                                                           1L72 3O      A7CE                         
20060627003142006062700314SO  2006       6          27         2006FA0000608    120060612G273062701159        CONTROL CABLE                           PIPER PA32  PA32RT300   7103215SO  LYC   0540  IO540K1G5D  41532SO                              ELEVATOR        SEPARATED       D      O   OTHER                                                                                           D  INFLIGHT SEPARATION                                                           LDLANDING        1                      SO16317092741                   32R7885121  L1809048A                   UP ELEVATOR CABLE SEPARATED IN LANDING FLARE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1L71 3O3  O  A3SO    1E4                  
20060627003152006062700315SO  2006       6          27         2006FA0000609    120060612G273062701159        CONTROL CABLE                           PIPER PA32  PA32RT300   7103215SO  LYC   0540  IO540K1G5D  41532SO                              ZONE 300        SEPARATED       D      O   OTHER                                                                                           D  INFLIGHT SEPARATION                                                           LDLANDING        1                      SO16317092741                   32R7885121  L1809048A                   UP ELEVATOR CABLE SEPARATED DURING LANDING FLARE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L71 3O3  O  A3SO    1E4                  
20060627003162006062700316SO  2006       6          27         2006FA0000610    120060612G273062701159        CONTROL CABLE                           PIPER PA32  PA32RT300   7103215SO  LYC   0540  IO540K1G5D  41532SO                              ZONE 300        SEPARATED       D      O   OTHER                                                                                           D  INFLIGHT SEPARATION                                                           LDLANDING        1                      SO16317092741                   32R7885121  L1809048A                   UP ELEVATOR CABLE SEPARATED DURING LANDING FLARE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L71 3O3  O  A3SO    1E4                  
20060627003172006062700317SO  2006       6          27         2006FA0000611    120060612G273062701159        CONTROL CABLE                           PIPER PA32  PA32RT300   7103215SO  LYC   0540  IO540K1G5D  41532SO                              ZONE 300        SEPARATED       D      O   OTHER                                                                                           D  INFLIGHT SEPARATION                                                           LDLANDING        1                      SO16317092741                   32R7885121  L1809048A                   UP ELEVATOR CABLE SEPARATED DURING LANDING FLARE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L71 3O3  O  A3SO    1E4                  
20060627003182006062700318CE  2006       6          27         2006FA0000612    120060621G53111054200116      FRAME                                   BEECH 76    76          1153005CE                                                               RT WINGFEATHERINCRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO09141P 2269                   ME237                                   CRACK IN RT FORWARD WING BOLT ATTACH FRAME, P/N: 105-420011-6.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L72 3O      A29CE                        
20060627003192006062700319CE  2006       6          27         2006FA0000613    120060621G53111054200116      FRAME                                   BEECH 76    76          1153005CE                                                               RT WING         CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO09141P 2269                   ME237                                   CRACK IN RT FWD WING BOLT ATTACH FRAME, P/N: 105-420011-6.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L72 3O      A29CE                        
20060627003212006062700321CE  2006       6          27         2006FA0000614    120060621G53111054200116      FRAME                                   BEECH 76    76          1153005CE                                                               ZONE 100        CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO09141P 2269                   ME237                                   CRACK IN RT FWD WING BOLT ATTACH FRAME, P/N: 105-420011-6.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L72 3O      A29CE                        
20060627003222006062700322CE  2006       6          27         2006FA0000615    120060621G53111054200116      FRAME                                   BEECH 76    76          1153005CE                                                               ZONE 100        CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO09141P 2269                   ME237                                   CRACK IN RT FWD WING BOLT ATTACH FRAME, P/N: 105-420011-6.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L72 3O      A29CE                        
20060627003232006062700323CE  2006       6          27         2006FA0000616    120060621G53111054200116      FRAME                                   BEECH 76    76          1153005CE                                                               ZONE 100        CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO09141P 2269                   ME237                                   CRACK IN RT FWD WING BOLT ATTACH FRAME, P/N: 105-420011-6.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L72 3O      A29CE                        
20060627003242006062700324CE  2006       6          27         2006FA0000617    120060621G53111054200116      FRAME                                   BEECH 76    76          1153005CE                                                               ZONE 100        CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO09141P 2269                   ME237                                   CRACK IN RT FWD WING BOLT ATTACH FRAME, P/N: 105-420011-6.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L72 3O      A29CE                        
20060627003252006062700325    2006       6          27         2006FA0000618    120060623G26127503611         CONTROL PANEL                           AMD   STC   STCFALC50                                                                           FIRE DETECTION  FAILED          B      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            NRNOT REPORTED   1                      SW11223HD2811                   283                                     FIRE CONTROL PANEL FAILED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F      A46EU                        
20060627003262006062700326EU  2006       6          27         2006FA0000619    120060623G26127503611         CONTROL PANEL                           AMD   FALC50FALCON50MYST2730106EU                                                               FIRE DETECTION  FAILED          B      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         NRNOT REPORTED   1                      SW11223HD2811                   283                                     FIRE CONTROL PANEL FAILED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L73 4F      A46EU                        
20060627003272006062700327NM  2006       6          27         2006FA0000620    120060608G62305100400         HOSE                                    DOUG  MD900 MD900       3027375NM  PWC   PW207 PW207E           NE                              XMSN OIL        CRACKED         D      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      EA11902PD450                    9000084                                 PILOT NOTICED TRANSMISSION OIL PRESSURE INDICATION DROPPED FROM GREEN TO YELLOW TO RED.  MADE UNSCHEDULED LANDING. FOUND FWD LT TRANSMISSION OIL COOLER HOSE LEAKING. HOSE IS A FLEXIBLE STAINLESS STEEL HOSE WITH A STAINLESS STEEL OUTER BRAID. HOSE WAS INSPECTED AFTER REMOVAL AND FOUND TO BE CRACKED. REPLACED HOSE P/N 900D3409526-105.                                                                                                                                                                                                                                                                                                                                                                                                  1G72 3U3  UNCH19NM   E42NE                
20060627003282006062700328CE  2006       6          27         2006FA0000621    120060622G5730                SKIN                                    CESSNA414   414         2075908CE                                                               RT WING         CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15414JS6794                   4140811                                 DURING AN ANNUAL INSPECTION, A CRACK WAS FOUND ON THE RT WING SKIN AT THE OB AILERON ATTACH POINT, WHICH IS ALSO THE MAIN FUEL TANK AFT ATTACH POINT. UPON FURTHER INSPECTION OF AREA, THE RIVETS THAT ATTACH THE AILERON SUPPORT TO THE REAR SPAR WERE FOUND SHEARED, CAUSING THE MAIN TANK TO HAVE MOVEMENT. IF LEFT UNDETECTED, COULD CAUSE MAIN FUEL TANK STRESS AT THE FWD ATTACH POINTS, CRACKED REAR SPAR OR POSSIBLE SEPARATION OF THE TANK.                                                                                                                                                                                                                                                                                            1L72 3O    RTA7CE                         
20060627003292006062700329CE  2006       6          27         2006FA0000622    120060622G5730                SKIN                                    CESSNA414   414         2075908CE                                                               ZONE 600        CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15414JS6794                   4140811                                 DURING AN ANNUAL INSPECTION, A CRACK WAS FOUND ON THE RT WING SKIN AT THE OB AILERON ATTACH POINT, WHICH IS ALSO THE MAIN FUEL TANK AFT ATTACH POINT. UPON FURTHER INSPECTION OF AREA, THE RIVETS THAT ATTACH THE AILERON SUPPORT TO THE REAR SPAR WERE FOUND SHEARED, CAUSING THE MAIN TANK TO HAVE MOVEMENT. IF LEFT UNDETECTED, COULD CAUSE MAIN FUEL TANK STRESS AT THE FWD ATTACH POINTS, CRACKED REAR SPAR OR POSSIBLE SEPARATION OF THE TANK.                                                                                                                                                                                                                                                                                            1L72 3O    RTA7CE                         
20060705000252006070500025CE  2006       7          5          2006FA0000624    120060607G3200174302120       SHIMMY DAMPENER CESSNA                  CESSNA177   177B        2073708CE                                                               MLG             LEAKING         D      K   NONE                                                                                            KJ FLUID LOSS                WARNING INDICATION                                  ININSP/MAINT     1                      WP17345974025                   17701892                                PART BECAME SUSPECT WHEN DAMPENER FLUID WAS NOTICED DRIPPING OFF END OF SHAFT. DURING THE CLEANING/INSP. COMPRESSED AIR WAS INTRODUCED TO SHAFT'S OPEN END.  AIR BUBBLES WERE OBSERVED AT BASE OF PISTON. FOUND CRACK ON DAMPENER SHAFT AT BASE OF PISTON.  CRACK IS NOTICEABLE 360 DEGREES AROUND SHAFT EVEN THOUGH SHAFT IS STILL INTACT.  LOSS OF FLUID MAY HAVE EXAGGERATED VIBRATIONS CAUSING SHAFT TO FATIGUE OR MFG HEAT TREATING PROCESSES SINCE SHAFT IS NOT BROKEN COMPLETELY THROUGH.  INSPECT IMMEDIATELY IF FLUID IS SEEN DRIPPING FROM THE END OF THE SHAFT.  OR, REMOVE AND DYE PENETRANT INSPECT SHIMMY DAMPENER SHAFT AT NEXT 25/50 HOUR MAINTENANCE INTERVAL.                                                                 1H71 3O      A13CE                        
20060705003042006070500304EA  2006       7          5          2006FA0000625    120060620G2910604752383       TUBE                                    CNDAIRCL600 CL6002B16   1900305EA  GE    CF34  CF34*            NE                              HYD SYSTEM      CHAFED          B  JAVRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NE01881TW4180                   5348                                    PRESSURE LINE FROM NR 1 ENGINE DRIVEN PUMP CHAFED AT AFTMOST CLAMP LOCATION (NEAR NR 1 SYSTEM RESERVOIR) UNTIL THE LINE FAILED UNDER PRESSURE CAUSING A COMPLETE LOSS OF NR 1 HYDRAULIC SYSTEM IN FLIGHT.  CLAMP CUSHION FAILED CAUSING METAL TO METAL CONTACT.  SUSPECT THAT DEFECT WAS NOT READILY VISIBLE BEFORE FAILURE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F4  FRTA21EA   E15NE                
20060705000102006070500010CE  2006       7          5          2006FA0000626    120060612G2497K3A2            CABLE                                   CESSNA421   421A        2076012CE                                                               LT STARTER      SHORTED         B  AGERK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP0599VK                        421A0091                                DURING STARTING OF LT ENGINE, SMOKE WAS OBSERVED COMING FROM THE LOUVERS ON TOP OF THE LT ENGINE.  THE ENGINE WAS SHUTDOWN AND THE SMOKE SUBSIDED.  INSP REVEALED THAT THE 2-GAUGE STARTER AND ALTERNATOR POWER CABLES WERE BURNED IN HALF NEAR THE TURBOCHARGER.  FOURTEEN OTHER WIRES IN THE SAME BUNDLE WERE ALSO BURNED IN HALF OR SEVERELY HEAT DAMAGED.  THE ELECTRICAL FIRE WAS A RESULT OF THE STARTER CABLE SHORTING TO GROUND ON THE TURBO SUPPORT BRACKET (PN 5155101-20).  THE ELECTRICAL WIRE BUNDLE HAD BEEN RESTING ON THIS BRACKET FOR SOME TIME UNTIL THE WIRE INSULATION WAS CHAFFED THROUGH.  INSP OF THE OTHER ENGINE REVEALED SIMILAR CHAFFING AND POSSIBLILITY OF A SHORT.  (K)                                           1L72 3O      A7CE                         
20060711001052006071100105EA  2006       7          11         2006FA0000627    220060605G850071907           WASHER                                  PIPER PA25  PA25235     7102504SO  LYC   O540  O540*       41532EA                              COUNTER WEIGHT  CRACKED         G      O   OTHER                                                                                           Y  ENGINE STOPPAGE                                                               AGAGRICULTURE    1                      GL277785Z835  835               253989      L677440                     COUNTER WEIGHT RETAINING WASHER P/N 71907 CRACKED AND BROKE. THIS ALLOWED THE COUNTER WEIGHT RETAINING PIN TO FALL OUT. ENGINE SEIZED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L71 3O3  O  2A10    E295                 
20060705002942006070500294    2006       7          5          2006FA0000628    120060613G81204066109026      TURBOCHARGER                                                                                                                                            INOPERATIVE     B      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM07                                                                    TURBO WILL NOT PRODUCE BOOST.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        
20060705003032006070500303    2006       7          5          2006FA0000629    120060615G2420ALY6521         ALTERNATOR                                                                                                                                              INOPERATIVE     B      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM07                                                                    ALTERNATOR WOULD NOT ENGAGE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         
20060705000082006070500008EA  2006       7          5          2006FA0000630    220060612G7414ES10357174      CONTACT         BENDIX                  PIPER PA25  PA25235     7102504SO  LYC   O540  O540B2B5    41532EA                              MAG POINTS      BROKEN          D      A   UNSCHED LANDING                                                                                 R  PARTIAL RPM/PWR LOSS                                                          CRCRUISE         1                      GL094811Y44         6010962     254592      L713540                     MAG FAILED IN FLIGHT, UPON INSPECTION POINTS WERE FOUND TO BE BROKEN WITH 44 HOURS TT ON THE POINTS.  THE SPRING PORTION WAS BROKEN DUE TO A DEFECT IN THE STAMPING WHICH SET UP A STRESS POINT AT THE ATTACH SCREW.  RECOMMEND MFG CONTACT ASSY BE INSPECTED FOR PROPER BENDING OF THE PARTS AND REMOVE FROM SERVICE THAT DO NOT HAVE PROPER FORMING OF THE SPRING.  (K)                                                                                                                                                                                                                                                                                                                                                                       1L71 3O3  O  2A10    E295                 
20060705000132006070500013CE  2006       7          5          2006FA0000631    120060602G29101240016CR0164   LINE                                    BEECH 99    99A         1154003CE  PWA   PT6   PT6*        52043EA                              HYDRAULIC SYS   RUPTURED        B  TIMRA   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CLCLIMB          1                      NM07326CA                       U135                                    DURING CLIMBOUT THE (GEAR IN TRANSIT) AND (DO NOT REVERSE) ANNUNCICATOR ILLUMINATED AND THEN THE LANDING GEAR CIRCUIT BREAKER POPPED.  PILOT CONTINUED, HAND PUMPED THE GEAR TO GET 3 GREEN.  LANDED OK.  INVESTIGATION DETERMINED THAT HYDRAULIC HOSE ON THE LT UP LINE HAD RUPTURED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L72 3T3  T  A14CE   E2NE                 
20060705000032006070500003CE  2006       7          5          2006FA0000632    120060620G272000252400023     CONTROL CABLE                           BEECH 33    F33A        1151425CE  CONT  O520  IO520*      17032SO                              RUDDER          FRAYED          B  Y5VRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM058259C                       CE1763                                  AT ANNUAL INSP RT AFT RUDDER CABLE WAS FOUND FRAYED ALMOST IN TWO.  CABLE WAS FOUND ROUTED OVER THE TOP OF ONE CABLE PULLEY GUARD PIN, AND UNDER ANOTHER AT SAME LOCATION IN AFT TAIL SECTION.  CABLE REMOVED APPEARED TO BE THE ORIGINAL CABLE INSTALLED IN AIRCRAFT AT FACTORY.  LOGBOOKS DID NOT REVEAL ANY EVIDENCE THAT THE CABLE HAD EVER BEEN REMOVED OR DISCONNECTED THAT MAY HAVE CAUSE THIS.  BY THE AMOUNT OF CABLE THAT WAS FRAYED, IT APPEARS TO HAVE BEEN RUBBING ON THE PULLEY GUARD PIN FOR SOME TIME.  IT IS SUSPECTED THAT THIS CABLE WAS ROUTED INCORRECTLY AT THE FACTORY.  POSSIBLE QUICK FASHION ANNUAL PREVIOUS.  RECOMMEND THOROUGH ANNUAL IN ITS ENTIRETY.                                                             1L71 3O3  O  3A15    E5CE                 
20060705003062006070500306CE  2006       7          5          2006FA0000634    120060519G760045A431755       LINK                                    BEECH MU300 400A        1155402CE  PWA   JT15  JT15D5      52112NE                              LT ENGINE       WORN            D  EKGRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP07435CW                       RK35        PCE100250                   DURING OPERATIONAL CHECK FLIGHT OF AIRCRAFT, PILOT ADVANCED POWER LEVERS FORWARD AND NOTED LT ENG (N) REACHED MAX OF 117 PERCENT N2, REACHED MAXIMUM OF 100 PERCENT.  IT IS DETERMINED THAT PROBABLE CAUSE OF OVERSPEED WAS ACHIEVED BY WORN THROTTLE LEVER LINK NOT PROVIDING ACCURATE RANGE OF MOTION TO CORRECTLY ACTUATE THROTTLE STOP.  ENGINE LEVERS WERE ENABLE TO ADVANCE FURTHER THAN NORMAL, CAUSING OVERSPEED CONDITION.  IT IS RECOMMENDED THAT LINK AND ASSOCIATED HARDWARE BE REPLACED.  (K)                                                                                                                                                                                                                                      2H72 4F4  FRTA16SW   E25EA                
20060705002992006070500299EU  2006       7          5          2006FA0000635    220060608G72509514M71PO4      SHAFT                                   BOEING737   737300      1384610NM  CFMINTCFM56 CFM563C1    13802EU                              ENGINE          FRACTURED       B  QEMYK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA35B294330987                              857655                      REF: MRD/001/06 - AC CUFFERED AN ABORTED TAKEOFF.  INVESTIGATION REVEALED FAILURE AND LIBERATION OF THE HPT REAR SHAFT WHERE A SECTION OF MATERIAL MEASURING 3.5 INCH CIRCUMFERENCE HAD LIBERATED AROUND THE 3 SEAL TOOTH RACK.  SIMILAR FAILURES HAVE BEEN EXPERIENCED ON ENGINE.  PARTS ARE RETURNED TO MFG FOR INVESTIGATION.  EDDY CURRENT INSPECTION INTO 3Q95.  (K)                                                                                                                                                                                                                                                                                                                                                                       2L72 4F4  FRTA16WE   E21EU                
20060705003082006070500308    2006       7          5          2006FA0000636    220060501G7497                WIRE                                    DHAV  DHC8  DHC8*              NM                                                               EXCITER         FAILED          B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NE05          415   895                                                 EXCITER ROTOR LEAD WIRES BREAK AT SOLDER CONNECTION TO DIODE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2H72 4T    RTA13NM                        
20060705003092006070500309    2006       7          5          2006FA0000637    220060501G7497                WIRE                                    DHAV  DHC8  DHC8*              NM                                                               EXCITER         FAILED          B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NE05                392                                                 EXCITER ROTOR LEAD WIRES BROKEN AT SOLDER CONNECTION TO DIODES.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2H72 4T    RTA13NM                        
20060705002912006070500291EU  2006       7          5          2006FA0000638    120060621G2720NB45D1803       CONTROL ROD                             BNORM BN2   BN2A        1520204EU                                                               RUDDER          DAMAGED         I      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      SO17131JL25031                  225                                     AFTER TAKEOFF THE PILOT NOTICED THAT THE RUDDER HAD TO MUCH PLAY IN FLIGHT.  HE LANDED AND TAXIED BACK IN.  UPON INSPECTION THE RUDDER CONTROL ROD WAS FOUND TO BE DAMAGED, FROM A WIND STORM THE NIGHT BEFORE.  TO PREVENT REOCCURANCE, THE AIRCRAFT RUDDER SHOULD BE LOCKED IN PLACE AFTER EACH FLIGHT.                                                                                                                                                                                                                                                                                                                                                                                                                                       1H72 3O      A17EU                        
20060705003402006070500340EU  2006       7          5          2006FA0000639    120060525G7603L810BQ54        SOLENOID                                SNIAS 350   AS350B3     8680954EU  TMECA ARRIELARRIEL2B         NE                              THROTTLE SYS    MALFUNCTIONED   D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW15186AE                       3872        22484                       WHILE PERFORMING CHECK OF TWIST GRIP SOLENOID, ENGAGED SOLENOID BY PLACING THE AUTO/MAN SWITCH TO MAN MODE FOR A TOTAL OF 10 MINUTES.  AFTER 10 MINUTE PERIOD HAD ELAPSED.  RETURNED AUTO/MAN SWITCH TO AUTO.  AFTER 15 SECONDS, MOVED AUTO/MAN SWITCH BACK TO MAN, PISTON FROM SOLENOID FAILED TO MOVE.  PISTON SHOULD HAVE RETRACTED IMMEDIATELY.  SOLENOID OVERHEATED AND MALFUNCTIONED.  RECOMMENDATION TO PREVENT RECURRENCE: REPLACING CURRENT PN OF SOLENOID WITH ONE THAT CAN EITHER RUN COOLER OR WITHSTAND THE HEAT.  (K)                                                                                                                                                                                                             1G71 3U3  U  H9EU    E00054EN             
20060718001612006071800161NM  2006       7          18         2006FA0000640    120060705G510035006931        CARRIER ASSY                            DOUG  MD80  MD83        3023681NM                                                               UNKNOWN         CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW99                                                                    CARRIER PN 3500693-1 FOUND CRACKED DURING PENERANT INSPECTION OF PART. PART WAS BEING INSPECTED FOR OVERHAUL REPAIR, CRACK IS BEYOND REPAIR LIMITS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F    RT                             
20060718001682006071800168SO  2006       7          18         2006FA0000641    120060623G8011MZ4204R         STARTER                                 PIPER PA23  PA23160     7102304SO  LYC   O320  O320*       41508EA                              ENGINE          MISOVERHAULED   D      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      NM033341P                       231294                                  UPON RECEIPT OF STARTER, INITIAL INSPECTION REVEALED LOOSE HARDWARE ATTACHING FRONT HOUSING TO STATOR HOUSING. DISASSEMBLED UNIT AND FOUND TWO PIECES OF SOLDER IN ARMATURE AREA; ONE APPROX .2500 X .7500 X .0625 INCH, THE SECOND APPROX .2500 INCH X 2 INCHES X .0625 INCH. ALSO FOUND 1 OF 4 BRUSHES NOT SEATED IN BRUSH HOLDER AND NOT IN CONTACT WITH COMMUTATOR. FASTENER HOLES IN STATOR HOUSING WERE STRIPPED AS THOUGH FASTENERS WERE OVER-TORQUED TO SEAT FRONT HOUSING IN STATOR HOUSING. RECOMMEND RE-EVALUATE OVERHAUL PROCEDURES, QUALITY CONTROL, AND POST-OVERHAUL TEST PROCEDURES. RECOMMEND ALL OPERATORS CAREFULLY INSPECT COMPONENTS RECEIVED BEFORE INSTALLING ON AIRCRAFT.                                               1L72 3O3  O  1A10    E274                 
20060719000022006071900002EU  2006       7          19         2006FA0000643    120060609G275050B275103B      ROD                                     AMD   FALC50FALCON50MYST2730106EU  GARRTTTFE731TFE731*     01518WP                              TE FLAPS        CHAFED          B  JGVRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE0985TN 6712                   237                                     WHEN COMPLYING WITH SB, FOUND FLAP ROD LOCATED IN RT MAIN LANDING GEAR COMPARTMENT CHAFFED AT IB END.  FLAP ROD STIRRUP INSTALLED INCORRECT CAUSING ROD TO CHAFFE WHEN FLAPS ARE OPERATED.  REMOVED STIRRUP REPOSITIONED 180 DEGREES.  REINSTALLED AND REPLACED FLAP ROD WITH NEW.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L73 4F4  F  A46EU   E6WE                 
20060719000162006071900016CE  2006       7          19         2006FA0000644    120060628G531110581002367     FRAME                                   BEECH 76    76          1153005CE                                                               FUSELAGE        CORRODED        D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW996720T9119                   ME335                                   A-FRAME TUBE ASSY FAILED AT CORROSION PREVENTION PORT CAUSING LT MAIN GEAR COLLAPSE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 3O      A29CE                        
20060718001712006071800171CE  2006       7          18         2006FA0000646    120060628G534320410201        SUPPORT                                 CESSNA177   177RG       2073709CE  LYC   O360  IO360A1B6   41514EA                              MLG             BROKEN          C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP09177R 4400                   177RG0955                               MLG ACTUATOR SUPPORT WEB BROKEN AND CRACKED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1H71 3O3  O  A20CE   1E10                 
20060719000032006071900003CE  2006       7          19         2006FA0000647    120060628G323320410202        PIN                                     CESSNA177   177RG       2073709CE  LYC   O360  IO360A1B6   41514EA                              MLG ACTUATOR    BROKEN          C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP09177R 4400                   177RG0955                               ACTUATOR RETAINING PIN, FRACTURED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1H71 3O3  O  A20CE   1E10                 
20060719000082006071900008CE  2006       7          19         2006FA0000648    120060614G279735823071        CONNECTOR                               BEECH MU300 400A        1155402CE                                                               WIRE HARNESS    DAMAGED         B  E81RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03907JE                       RK107                                   INVESTIGATED REPORT OF FLAP ASYMMETRY ANNUNCIATOR LIGHT FLICKERING IN-FLIGHT.  FOUND WIRE C458A22 ROUTED SO THAT EXCESSIVE WIRE TENSION AT P156 PLUG WAS CAUSING INTERMITTENT CONTACT WITH A156 PC BOARD J1 CONNECTOR.  REROUTED WIRING AS REQUIRED FOR REVEALING WIRE TENSION AT P156 PLUG.  FLAP ASSYMETRY FUNCTIONAL TEST SATISFACTORY.  (K)                                                                                                                                                                                                                                                                                                                                                                                                 2H72 4F    RTA16SW                        
20060719000172006071900017CE  2006       7          19         2006FA0000649    120060622G21301013840283      SWITCH                                  BEECH 90    C90         1152913CE  PWA   PT6   PT6A60A     52043NE                              CABIN PRESSURE  OUT OF LIMITS   B  E81RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03261GB4490                   LJ1119                                  DURING SCHEDULED 12 MONTH TEST OF CABIN ALTITUDE WARNING SYSTEM FOUND BAROMETRIC SWITCH OPERATING OUT OF SPECIFIED MM.  REPLACED PN 1013384028-3 SWITCH ASSY.  CABIN ALTITUDE WARNING TESTS WITHIN SPECIFIED SERVICE LIMITS ON RETEST.  SUGGEST A SB BE ISSUED TO REPLACE OLDER PN BAROMETRIC SWITCHES THAT TEND TO FAIL BETWEEN TEST PERIODS WITH MORE RELIABLE SWITCHES.  (K)                                                                                                                                                                                                                                                                                                                                                                 1L72 3T4  T  3A20    E4EA                 
20060718001592006071800159    2006       7          18         2006FA0000650    420060620G2312CI108           ANTENNA                                 BEECH MU300 400A        1155402CE  PWA   JT15  JT15D5      52112NE                              FUSELAGE        DEBONDED        B  E81RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03731TA                       RK273                                   INVESTIGATED PILOT REPORT OF LOSS OF NR 1 AND NR 2 VHF COMMUNICATION RADIOS WHEN FLYING IN PRECIPITATION.  IAW P-STATIC TESTING FOUND POOR NR 1 AND NR 2 VHF ANTENNAS BONDS TO FUSELAGE.  CLEANED, REBONDED AND REINSTALLED ANTENNAS.  ALSO INSTALLED LT FUEL VENT LINE BONDING JUMPER.  P-STATIC TESTS AND OPERATIONAL TESTS SATISFACTORY AFTER REPAIRS.  SUGGEST VHF ANTENNAS BE REMOVED AND CLOSELY INSPECTED AT SCHEDULED INTERVALS, SUCH AS AN INITIAL 5000 HR OR 10 YEAR INSPECTION, FOLLOWED BY RECURRING 1200 HR OR 2 YEAR INTERVALS (IN CONUNCTION WITH C-CHECK INSPECTIONS).                                                                                                                                                          2H72 4F4  FRTA16SW   E25EA                
20060721002982006072100298NE  2006       7          21         2006FA0000651    220060628G72503028601         BLADE                                                                      PWA   JD15  JT15D1A          NE                              ENGINE          SEPARATED       D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW15     2818                               PCE76791                    DURING POST LEASE INSPECTION, FOUND 1 HIGH TURBINE BLADE SEPARATED AT MID SPAN.  APPARENTLY NO OPERATIONAL PROBLEMS.  MFG HAS PRODUCED REPLACEMENT BLADES UNDER SPARE PARTS BULLETIN 75.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          4  F          E25EA                
20060711001122006071100112CE  2006       7          11         2006FA0000652    120060601G2620                GAUGE                                   LEAR  45    45LEAR      5170805CE  GARRTTTFE731TFE7315BR        WP                              FIRE BOTTLE     BROKEN          B  KW3RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP07456Q                        282                                     THIS THE THIRD FIRE BOTTLE FOUND, ON 2 DIFFERENT AIRCRAFT WITH THE PRESSURE GAUGE SCALE BROKEN FREE FROM ITS MOUNTED POSITION.  THE RESULT WAS A FALSE INDICATION OF AGENT (HALON CBRF3) PRESENT INSIDE THE BOTTLE.  THE LOCAL QA MANAGER IS LAUNCHING A FORMAL INVESTIGATION WITH THE MFG QA.  FORTUNATELY THIS AC WAS NOT INVOLVED IN AN ACCIDENT OR INCIDENT.  GOOD ROOT CAUSE ANALYSIS AND CRITICAL THOUGHT FOUND THIS DEFECT.  (K)                                                                                                                                                                                                                                                                                                         2L72 4F4  FRTT00008WIE6WE                 
20060721001322006072100132    2006       7          21         2006FA0000653    220060626G7414                                SLICK                                                                                                                                                   B  WS9RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM07                05111170                                            HIGH MAGNETO DROP.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   
20060719000062006071900006    2006       7          19         2006FA0000654    120060621G81204066109005      TURBOCHARGER                                                                                                                            ENGINE          LEAKING         B  WS9RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM07                                                                    LEAKING BETWEEN HOT AND COLD SECTION.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                
20060718001652006071800165GL  2006       7          18         2006FA0000655    120060608G3210750B            POWERPACK                               BLANCA1419  1419        1220402GL  LYC   O435  O435A       41516EA                              LANDING GEAR    STUCK           G      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM096561N                       2014                                    RELIEF VALVE IN LANDING GEAR POWER PACK WAS STUCK.  WOULD NOT ALLOW LANDING GEAR HYDARULIC SYSTEM PRESSURE TO BE RELIEVED TO ALLOW GEAR TO EXTEND.  RESULT GEAR UP LANDING.  POST INCICENT TESTING VALVE WORKED NORMALLY. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1L71 3O3  O  1A3     E228                 
20060718001662006071800166NE  2006       7          18         2006FA0000656    220060620G7200TFE73160        ENGINE                                  AMD   FALC90FALCON900EX 2730009EU  GARRTTTFE731TFE73160         NE                              NR 1            DAMAGED         G      A   UNSCHED LANDING                                                                                 XJ ENGINE FLAMEOUT           WARNING INDICATION                                  DEDESCENT        1                      SO19977LP1317                   77          P112347                     AT FL350, AIRCRAFT EXPERIENCED A LOUD BANG AND FAILURE OF NR 1 ENGINE (ITT WENT TO RED AND N1 APPROXIMATELY 20 PERCENT).  ENGINE WAS SHUTDOWN.  DURING DESCENT EXPERIENCED VIBRATION IN AIR FRAME AND CONTROL COLUMN.  POST FLIGHT INSPECTION REVEALED EXTENSIVE DAMAGE TO THE NR 1 ENGINE REAR TURBINE BLADES AND COOKIE CUTTER.  NO EXTERNAL DAMAGE WAS NOTED.  ENGINE WAS REPALCED.  (K)                                                                                                                                                                                                                                                                                                                                                     2L73 4F4  FRTA46EU   E1NM                 
20060721001562006072100156NM  2006       7          21         2006FA0000657    120060720G575165192613        SUPPORT                                 BOEING727   72725C      138400HNM  PWA   JT8   JT8D5       52046NE                              LT AILERON      CRACKED         B  NP1YK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA33932UP53694                  19856                                   DURING C-CHECK ROUTINE INSPECTION A 1 INCH CRACK (APPROX) WAS FOUND IN LT OB AILERON LOCKOUT MECHANISM SUPPORT ASSY CASTING IN THE RADIUS AREA OF THE AILERON CRANK PIVOT POINT.  SUPPORT ASSY IS BEING REPLACED BY ASSY PN 65-2177613. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L73 4F4  F  A3WE    E2EA                 
20060719000042006071900004SO  2006       7          19         2006FA0000658    220060710G7313652312112E      NOZZLE                                  TCRAFTBC    BC12D       8850316GL  CONT  O550  IO550N      17042SO                              FUEL SYSTEM     CRACKED         G      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NE03716B                        7919                                    DURING MAINTENANCE THE MECHANIC WAS REPLACING THE FUEL INJECTION NOZZLES DUE TO THE REQUEST OF THE OWNER.  THE OWNER WANTED TO INSTALL A NEW KIT THE POSITION-TUNED FUEL INJECTION NOZZLES IAW THE ID SID05-7.  DURING THE INSTALLATION OF THESE NOZZLES 1 CRACKED PRIOR TO REACHING THE TORQUE VALUE AS LISTED IN SID05-7.                                                                                                                                                                                                                                                                                                                                                                                                                     1H71 3O3  O  A696    E3SO                 
20060719000202006071900020EA  2006       7          19         2006FA0000660    220060710G7414                BUSHING                                 PIPER PA32  PA32300     7103212SO  LYC   O540  IO540*      41532EA                              MAGNETO         FAILED          D      B   EMER. DESCENT                                                                                   RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  NRNOT REPORTED   1                      SW0770746469  469   H279705FR   3240521                                 MAGNETO'S DISTRIBUTOR GEAR BUSHING FAILED RESULTING IN AN ACCIDENT. MAGNETO LAST OVERHAULED EIGHT YEARS BEFORE. DFW06LA172                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L71 3O3  O  A3SO    1E4                  
20060725001832006072500183    2006       7          25         2006FA0000662    120060629G6510538715          SHAFT                                                                                                                                   TAIL ROTOR      CRACKED         C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP23                                                                    MAGNETIC PARTICLE INSPECTION 7 PCS WITH TRANSVERSE CRACKS INDICATIONS ON O.D. OF THE PART                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 
20060718001702006071800170CE  2006       7          18         2006FA0000665    120060711G3220                LANDING GEAR                            BEECH 35    35BEECH     1151502CE                                                               NOSE            COLLAPSED       C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW99                            D2053                                   NOSE LANDING GEAR COLLAPSED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L71 3O      A777                         
20060725002392006072500239SO  2006       7          25         2006FA0000666    220060623G8550629218          IMPELLER                                CESSNA206   TU206F      2073353CE  CONT  O520  TSIO520M    17040SO  MCAULYD3A34 D3A34C401   GL  OIL SYSTEM      MISMANUFACTURED C      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      WP075090138                     U20601951   532305      972059          INSTALLED NEW ENGINE  FOLLOWED RECOMMENDED PROCEDURES FOR BREAK IN.  REMOVED & CUT OPEN OIL FILTER AT 1.4 HRS TTSN, AT 7.9HRS, & AT 24.7HRS. NORMAL PRACTICE WITH A NEW OR OVERHAULED ENGINE. EACH TIME FILTERS WERE NORMAL FOR A NEW ENGINE.  ACFT DUE A 100 HR INSPECTION AT 38.9HRS TTSN. DURING INSPECTION, EXCESSIVE METAL APPEARED TO BE BRASS NOTED IN OIL FILTER. TOOK OFF STARTER DRIVE & FOUND NO PROBLEMS. TOOK OFF ROCKER COVERS TO SEE IF A ROCKER ARM BUSHING BAD. DISCOVERED THAT BUSHINGS IN OIL PUMP DRIVEN IMPELLER EXCESSIVELY WORN.  IMPELLER WOULD CONTACT AN EDGE WITHIN PUMP. RECEIVED NEW PUMP ASSY. BEFORE INSTALLING PUMP PREFORMED DIMENSIONAL INSPECT OF IMPELLER & SHAFT, WITHIN NEW PARTS LIMITS. FLEW THE ACFT FO1H71 3O3  O  A4CE    E8CE    5  CP47GL    
20060718001732006071800173EA  2006       7          18         2006FA0000667    220060707G731415473           PUMP                                    AMTR  VANRV4VANSRV4            GL  LYC   O360  IO360A1A    41514EA  HARTZLHCM2Y HCM2YR      GL  FUEL SYS        FAULTY          G      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      GL11342MG19                     1863        L136451A                    T/O ROLL OK, ENG STARTED LOSING PWR JUST AFTER T/O AT APROX 150 FT, DETECTED A SLIGHT MISS OR LOSS OF PWR, MADE A SHARP LT TURN , ENG CONTINUED TO LOSE PWR, SWITCHED ON BOST PUMP AT THIS TIME, ENG SEEMED TO RESPOND FOR A SECOND, BUT CONTINUED TO LOSE PWR, MADE ANOTHER LT, LANDED, PULLED AC BACK TO HANGER.  AC HAS VISION VM1000 INSTRUMENT.  CKD LAST FLT READINGS, FUEL PRES LOW 18 PSI, HIGH OF 29 PSI. RESTARTED ENG, IDLE WAS OK, FUEL PRESS WAS JUMPING FROM 20 TO 31 PSI.  PWR WAS INCREASED TO FULL PWR, HELD APROX 30 SECONDS, ENG STARTED LOSING PWR, BOOST PUMP ON NO CHANGE. TURNED BOOST PUMP OFF, WATCHED FUEL PRESS, IT WAS JUMPING FROM 19 TO 31 PSI THEN DOWN TO 23.   BYPASSED ENG DRIVEN PUMP AND ENG RAN, HELD PWR. 1L71 3O3  O  EXPA1L711E10    5  CP43GL    
20060718001812006071800181    2006       7          18         2006FA0000668    420060630G6113                SPINNER                                 BEECH 300   300BEECH    1152930CE                                   HARTZLHCB4M HCB4MP3     GL  RT PROPELLER    BROKEN          B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NE05603WM                       FA198                   FWA2935         RT PROPELLER WAS OVERHAULED AND INSTALLED IN THE RT POSITION.  ENGINE RAN TO LEAK CHECK AND FUNCTIONAL CHECK PROPELLER SYSTEM ON THE RT SIDE AND TO FULL POWER FOR APPROXIMATELY 60 SECONDS. A SLIGHT CHANGE IN THE HARMONICS WAS NOTED BUT NOT A SIGNIFICANT CHANGE.  AIRCRAFT RETURNED TO HANGER AFTER THE MAINTENANCE RUN UP AND A LEAK CHECK WAS PERFORMED.  IT WAS NOTED THAT ONE BLADE HAD A LARGE AMOUNT OF GREASE ON THE BLADE FACE.  THE SPINNER WAS REMOVED AND IT WAS FOUND BY VISUAL INSPECTION THAT A BLADE CLAMP BOLT HAD BROKEN AT THE HEAD.  THE HEAD OF THE BOLT WAS RECOVERED LODGED IN THE HUB AND BULKHEAD AREA.  THE BOLT P/N ACA-1372.                                                                                    2L72 4T      A24CE           6  CP56GL    
20060719000112006071900011CE  2006       7          19         2006FA0000669    120060712G3211NAS15288        CONE BOLT                               CESSNA188   188B        2073007CE                                                               LT MLG          FAILED          G      D   RETURN TO BLOCK                                                                                 O  OTHER                                                                         TXTAXI/GRND HDL  1                      SW174996R                       18802483T                               LT LANDING GEAR STRUT IB ATTACHMENT BOLT HEAD POPPED OFF DURING TAXI CAUSING PARTIAL GEAR COLLAPSED                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L71 3O      A9CE                         
20060719000182006071900018    2006       7          19         2006FA0000670    420060622G3460                COMPUTER                                AMD   FALC50FALCON2000  2730170NM                                                               FLT MANAGEMENT  INTERMITTENT    B      A   UNSCHED LANDING                                                                                 GJ MULTIPLE FAILURE          WARNING INDICATION                                  CRCRUISE         1                      SW11620MS                       31                                      ALL 3 FMS INTERMITTENTLY RESETS IN FLIGHT WITH INFORMATION RETURNING AT RANDOM.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2K72 4F    RTA50NM                        
20060719000192006071900019    2006       7          19         2006FA0000671    220060627G74146364            MAGNETO                                                                                                                                 ENGINE          FAILED          B  S4CRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP25                                                                    DEFECTIVE COIL WINDINGS FOUND. SECONDARY READINGS INDICATE DISCONTINUOUS INTERNAL CONDUCTORS. READINGS VARIED FROM NO RESISTANCE (INDICATING AN OPEN CIRCUIT) TO VERY HIGH, OUT OF TOLERANCE OHMS OF RESISTANCE (20 TIMES NORMAL). OHMMETER WAS CALIBRATED RECENTLY, CROSS REFERENCED AGAINST OTHER COILS TO VERIFY TEST EQUIPMENT USED, WAS STILL FUNCTIONING DURING THIS INSP.  OPERATOR OF THIS COMPONENT REPORTED NO DETECTABLE OPERATIONAL MALADIES. SECONDARY WINDING FAILURES MAY AFFECT ENG STARTING, PRODUCE MISFIRING, OR NON-OPERATIONAL IGNITION FROM THE AFFECTED MAGNETO. O.E.M. TYPE (TORQUE SEAL) PRODUCT INTACT AT TIME OF INSP, INDICATING NO INTERNAL MAINT OR INSP SINCE MAGNETO WAS MANUFACTURED.                                                                    
20060719000862006071900086CE  2006       7          19         2006FA0000672    120060104G3260IN4001          DIODE                                   CESSNA210   210M        2073450CE  CONT  O520  IO520L      17032SO  MCAULY3A32C D3A32C88    GL  WARNING UNIT    INOPERATIVE     G      O   OTHER                                                                                           N  FALSE WARNING                                                                 LDLANDING        1                      SO19LVWHD                       21061943    270473R     900308          DURING LANDING, FORGOT TO EXTEND THE LANDING GEAR AND GEAR UP LANDING WAS CARRIED OUT.  ACCIDENT INVESTIGATION INCLUDED A SATISFACTORY OPS CHECK OF LANDING GEAR RETRACTION/EXTENSION SYSTEM, BUT WARNING HORN FAILED TO OPERATE.  AFTER DISASSEMBLING THE WARNING UNIT ASSEMBLY, A BURNED DIODE WAS FOUND OUT.  THEN CONSULTED SM AND REALIZED THAT THERE IS NOT A SPECIFIC ITEM TO CHECK THE OPERATION OF THE GEAR WARNING HORN.  THIS SITUATION ALSO TAKES PLACE WITH MFG SRM.  GEAR INDICATOR LIGHT AND WARNING HORN-CHECK FOR OPERATION (GEAR EXTENDED AND RETRACTED).                                                                                                                                                                     1H71 3O3  O  3A21    E5CE    5  CP21EA    
20060721001302006072100130WP  2006       7          21         2006FA0000673    220060316G726031080412        BEARING         GARRTT                  SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE33111U   01514WP                              ENGINE          CORRODED        B  X2ZRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL25438MA           P44090C     AC721B      P44090C                     DUE TO CHIP LIGHT ILLUMINATION. TEST RUN COMPLETED. TORQUE SYS CALIBRATION AND ALL REQUIRED FUNCTIONAL/LEAK CHECKS CARRIED OUT.  NEW TORQUE DATA ISSUED.  NTS TRIF CK REQUIRED PRIOR TO RETURN TO SERVICE.  PERFORMED SOAP SAMPLE WITHIN 10-25 OPERATING HRS.  FAILURE OF ACCY GEAR ASSY BRG WAS ATTRIBUTED TO RUST PITTING ON ROLLING ELEMENT SURFACES.  SIMILAR PITTING WAS FOUND ON FWD PROP SHAFT BRG WITH SPALLING.  LOOSENING OF ONE PLANETARY PIN CAUSED CHAFFING OF PIN AND SCORING OF CARRIER.  ALL REMAINING BRGS IN ENGINE WERE DISASSEMBLED FOR INSP.  ALL BRGS WITH RIVETED CAGES WHICH DID NOT ALLOW FOR INSP WERE REPLACED AS A PRECAUTIONARY MEASURE DUE TO SUSPECTED RUST PITTING.                                             2L72 4T4  TRTA8SW    E4WE                 
20060721003712006072100371CE  2006       7          21         2006FA0000674    120060612G2720031019613       SPRING                                  CESSNA150   152         2071835CE  LYC   O235  O235*       41505EA                              RUDDER PEDALS   BROKEN          B  C85RO   OTHER                                                                                           F  FLT CONT AFFECTED                                                             CRCRUISE         1                      NE0194467677                    15285682                                FLIGHT INSTRUCTOR WAS DEMO-ING A STALL TO STUDENT.  MANUVER STARTED AT 2700 FT.  CONTROLS LOCKED UP- AC WENT NOSE DOWN.  FLT INST RECOVERED AT 700 FT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1H71 3O3  ONT3A19    E223                 
20060721001312006072100131EA  2006       7          21         2006FA0000675    220060703G8540                BUSHING                                 MOONEYM20   M20J        5870219SW  LYC   O360  IO360A3B6   41514EA                              ENGINE          SPUN            B  X18RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NE013860H932                    241044      L2178051A                   FOUND DURING ANNUAL INSP, AN ALUMINUM BUSHING THAT IS LOCATED IN  ACCESSORY CASE, WHERE MAGNETO DRIVE GEAR IS LOCATED HAD BECOME LOOSE IN CASE AND SPUN.  FOUND THIS PROBLEM, WERE NOT ABLE TO INSTALL MAGNETO  CORRECTLY, WHEN MAGNETO WAS INSTALLED, IMPULSE COUPLING WOULD SOMETIMES NOT ENGAGE.  FOUND AT LAST OVERHAUL, ACCESSORY CASE WAS SENT OUT FOR OVERHAUL TO ECI.  TALKING TO TEAR DOWN PERSONNEL, SAID THAT THIS IS AN APPROVED REPAIR TO INSTALL AN ALUMINUM BUSHING IF IT IS DONE CORRECTLY, THERE SHOULD HAVE BEEN A DRILLED HOLE IN THE BUSHING FOR LUBRICATION, BUT NO HOLE. THUS NOT ALLOWING LUBRICATION TO BUSHING AREA, ALLOWING EXCESSIVE WEAR AND PART FAILURE.  SUGGEST WELDING AREA AND DRILLING  NEW BOSS.  (K)      1L71 3O3  O  2A3     1E10                 
20060721001632006072100163EU  2006       7          21         2006FA0000676    120060706G6123A3496           SPRING                                  STBROSSD3   SD360       8100606EU                                   HARTZLHCB5M HCB5MP3     GL  FEATHER SYSTEM  BROKEN          B  ME4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO19     156193801                                      EV755           FEATHERING SPRING WAS FOUND TO BE BROKEN WHILE STILL INSTALLED IN SPRING KIT.  THE SPRING BROKE IN 3 DIFFERENT PIECES.  KIT WAS DISASSEMBLED AND INSPECTED FOR FURTHER DAMAGE.  NOTE:  PROPELLER WAS REMOVED FROM SERVICE 08-DEC-00.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2H72 4T      A41EU           6  CP44GL    
20060721001372006072100137GL  2006       7          21         2006FA0000677    120060701G782014836001        MUFFLER                                 CIRRUSSR    SR22        2130001GL  CONT  O550  IO550N      17042SO                              EXHAUST         DETERIORATED    C  QRQRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW05752C                        0421        686750                      REPLACED LT MUFFLER ON AIRCRAFT DO TO THE DETERIORATED CONDITION OF THE SPARK ARRESTER INSIDE OF THE MUFFLER.  LT SIDE SPARK ARRESTER MELTED AND FOLDED OVER.  LT MUFFLER, PN 14836001.  THE FIRST DETECT REPORT WAS FILED WHEN AC HAD A TT 682 HRS.  BOTH LT AND RT SPARK ARRESTERS HAD FOLDED OVER AGAIN.  THATS 413 HRS SINCE LAST TIME.  RECOMMEND MANDITORY REPLACEMENT AT A SPECIFIED TIME OR REDESIGN OF ARRESTERS.  (K)                                                                                                                                                                                                                                                                                                                 1L71 3O3  ONTA00009CHE3SO                 
20060725002432006072500243SO  2006       7          25         2006FA0000678    120060713G32107521604         FORK                                    PIPER PA42  PA421000    7104225SO  GARRTTTPE331TPE331*     01514WP                              LT MAIN GEAR    CRACKED         D  FO7RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO134WE  1934                   425527041                               PILOT REPORTED A LEAKING LT MAIN GEAR STRUT, BUT WAS LEAKING FROM JOINT BETWEEN ALUMINUM FORK ASSY AND CHROMED STEEL STRUT TUBE.  STRUT DISASSEMBLED AND A RADIAL CRACK WAS FOUND, 2 INCH LOGN AND .5 INCH.  BELOW TOP OF ALUMINUM FORK ASSY.  A SERIOUS ACCIDENT COULD RESULT IF THE FORK ASSY DETACHED UPON LANDING.  NO DAMAGE OR HARD LANDINGS REPORTED.  (K)                                                                                                                                                                                                                                                                                                                                                                               1L72 4T3  TRTA23SO   E2WE                 
20060721003302006072100330EA  2006       7          21         2006FA0000679    220060626G7260                CHIP DETECTOR                           BELL  412   412EP       1182205SW  PWA   PT6   PT6*        52043EA                              NR 1 ENGINE     CONTAMINATED    C      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      SO15413EV                       36381       CPPSTH0691                  AC EXPERIENCED NR 1 ENG CHIP LIGHT.  MASTER CAUTION WAS EXTINGUISHED, LIGHT WENT OUT.  ABOUT 2 SECONDS LATER LIGHT CAME BACK ON WITH MASTER CAUTION, WAS AGAIN EXTINGUISHED, WENT OUT THEN CAME BACK ON.  PILOT ELECTED RETURN TO BASE.  AFTER LIGHT CAME ON AGAIN FOR 4TH OR 5TH TIME IN 2 MINUTES, PILOT DECIDED TO SECURE ENG, FUEL VALVES AND BOOST PUMPS WERE LEFT ON, IN EVENT THAT THEY NEED TO RESTART ENG.  ENG HAD JUST COME OUT OF 300 HR INSP, FLIGHT TO BASE, LANDING WAS UNEVENTFUL.  MAINT WAS DISPATCHED, INSPECTED CHIP PLUGS, FOUND A SMALL SILVER ON PLUG.  SILVER WAS REMOVED, CHIP PLUG WAS REINSTALLED, SAFETY WIRED.  AC WAS 20 MINUTE RUN CHECK FOR ANY ADDITIONAL CHIP LIGHTS AND WAS RELEASED BACK INTO SERVICE.  (K) 1G72 4U3  T  H4SW    E2NE                 
20060721002972006072100297CE  2006       7          21         2006FA0000680    120060622G2510551900922       SEAT FRAME                              CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              CHAIR           CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE05982NA                       5500345                                 UPPER CHAIR BASE ASSEMBLY CRACKED AT CHAIR BACK ATTACH POINTS.  CHAIR WAS REPAIRED IAW STRUCTURAL SEAT REPAIR.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L72 4F4  F  A22CE   E1NE                 
20060721003242006072100324CE  2006       7          21         2006FA0000681    120060601G521005170392        HANDLE                                  CESSNA206   U206F       2073333CE                                                               REAR DOOR       DEFECTIVE       D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL05736                         U20601781                               DOOR HANDLE WAS SPINNING INDEPENDENTLY OF THE MECHANISM FOR THE DOOR LATCH.  THE PORTION OF THE HANDLE WITH THE SPLINE IS PRESSED INTO THE HANDLE.  THE PRESS FIT WAS DEFECTIVE ALLOWING THE HANDLE TO SPIN FREELY.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1H71 3O      A4CE                         
20060724000392006072400039SO  2006       7          24         2006FA0000682    220060717G8520                CRANKCASE       CONT                    CESSNA401   401B        207590ECE  CONT  O520  TSIO520E    17040SO                              ENGINE          CRACKED         E      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW177916Q798  798   182575      401B0016    182575                      FOUND A CRACK IN BOTH CASE HALF AT THE FOURTH AFT BOLT HOLE FROM FRONT OF CASE AT 12 O'CLOCK POSITION. CRACKS WERE FOUND ON AN INSPECTION OF ENGINE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L72 3O3  O  A7CE    E8CE                 
20060724000572006072400057SO  2006       7          24         2006FA0000683    220060717G8520                CRANKCASE       CONT                    CESSNA401   401B        207590ECE  CONT  O520  TSIO520E    17040SO                              ENGINE          CRACKED         E      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW177916Q798  798   182575      401B0016    182575                      FOUND A CRACK IN BOTH CASE HALVES AT THE FOURTH AFT BOLT HOLE FROM FRONT OF CASE AT 12 O'CLOCK POSITION. CRACKS WAS FOUND ON AN INSPECTION OF ENGINE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L72 3O3  O  A7CE    E8CE                 
20060725001852006072500185CE  2006       7          25         2006FA0000684    120060717G555104320052        FITTING                                 CESSNA150   150M        2071830CE  LYC   O320  O320E2D     41508EA                              RT STAB         MISINSTALLED    D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL077765U5510                   15077837                                ON PREFLIGHT INSP, APPLIED A +/- 5 LB UP AND DOWN FORCE ON RT STABILIZER TIP, HEARD A GRUNTING SOUND.   FURTHER INVESTIGATION REVEALED A SMALL RELATIVE MOTION BETWEEN STABILIZER  AFT FITTING, 0432005-2, AND FUSELAGE.   REMOVING NUT OPENED A 0.020 INCH AIR GAP BETWEEN FITTING AND FUSELAGE. CLEANING GAP WITH A CLOTH DIDNT SHOW ANY METAL PARTICLES. THE FIX WAS TO FABRICATE A 0.020 INCH SHIM. THIS FITTING IS A VERY  RIGID CHANNEL SUCH THAT IF THERE WAS AN AIR GAP IT MAY NOT CLAMP ON TO THE FUSELAGE FITTING HARD ENOUGH WITH BOLT TORQUE. THIS MAY NOT BE A DEFECTIVE PART, JUST TOLERANCE STACK UP.  LEFT SIDE FITTING WAS CHECKED.  IT REQUIRED A 0.010 INCH SHIM.  THESE 2 AFT MNT POINTS ARE LOAD CYCLED MORE FREQUENTLY.  1H71 3O3  O  3A19    E274                 
20060725001862006072500186CE  2006       7          25         2006FA0000685    120060717G555104320052        FITTING                                 CESSNA150   150M        2071830CE  LYC   O320  O320E2D     41508EA                              RT STAB         LOOSE           D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL077765U5510                   15077837                                ON PREFLIGHT INSP, APPLIED A +/- 5 LB UP AND DOWN FORCE ON RT STABILIZER TIP AND HEARD A GRUNTING SOUND.   FURTHER INVESTIGATION REVEALED A SMALL RELATIVE MOTION BETWEEN STABILIZER AFT FITTING, 0432005-2, AND FUSELAGE.  REMOVING NUT, OPENED A 0.020 INCH AIR GAP BETWEEN THE FITTING AND FUSELAGE.  CLEANING GAP WITH A CLOTH DIDNT SHOW ANY METAL PARTICLES. FIX WAS TO FABRICATE A 0.020 INCH SHIM.  FITTING IS A VERY  RIGID CHANNEL THAT IF THERE WAS AN AIR GAP IT MAY NOT CLAMP ON TO FUSELAGE FITTING HARD ENOUGH WITH BOLT TORQUE.  THIS MAY NOT BE A DEFECTIVE PART, JUST TOLERANCE STACK UP.  LT SIDE FITTING WAS CHECKED.  IT REQUIRED A 0.010 INCH SHIM.THESE 2 AFT MOUNTING POINTS ARE LOAD CYCLED MORE FREQUENTLY.          1H71 3O3  O  3A19    E274                 
20060724000862006072400086GL  2006       7          24         2006FA0000686    320060714G6110ACA1373         NUT                                                                                                         HARTZLHCB4M HCB4M       GL  PROPELLER       FAILED          B  JGVRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09                                                    FWA2178         WHEN TORQUING OUTER CLAMP NUT P/N ACA1373, 1 EACH NEW OUTER CLAMP NUT THREADS FAILED BEFORE REACHING SPECIFIED TORQUE. PROPELLER WAS BEING REASSEMBLED DURING OVERHAUL. ASSEMBLED USING CALIBRATED TOOLS AND NEW HARDWARE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   6  CP56GL    
20060725002492006072500249CE  2006       7          25         2006FA0000687    120060714G5347                SEAT TRACK                              CESSNA180   180A        2072604CE                                                                               DAMAGED         H      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP23180LG                       32693                                   A BOLT WAS INSTALLED ON THE FORWARD MOST HOLE ON THE SEAT TRACK FOR USE AS A FORWARD STOP.  THE SEAT COULD BE POSITIONED OVER THE HOLE AND THE SEAT LOCKING PIN WOULD ENGAGE, BUT NOT FULLY DUE TO THE BOLT PASSING THROUGH THE HOLE.  THE MFG DESIGN DOES NOT ALLOW THE PIN TO ENTER THROUGH THE SEAT STOP HOLE.                                                                                                                                                                                                                                                                                                                                                                                                                               1H71 3O      5A6                          
20060725002522006072500252CE  2006       7          25         2006FA0000688    120060714G5347                SEAT                                    CESSNA180   180A        2072604CE                                                                               MISINSTALLED    H      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             TOTAKEOFF        1                      WP23180LG                       32693                                   A BOLT WAS INSTALLED ON THE FORWARD MOST HOLE ON THE SEAT TRACK FOR USE AS A FORWARD STOP.  THE SEAT COULD BE POSITIONED OVER THE HOLE AND THE SEAT LOCKING PIN WOULD ENGAGE, BUT NOT FULLY DUE TO THE BOLT PASSING THROUGH THE HOLE.  THE MFG DESIGN DOES NOT ALLOW THE PIN TO ENTER THROUGH THE SEAT STOP HOLE.                                                                                                                                                                                                                                                                                                                                                                                                                               1H71 3O      5A6                          
20060724000432006072400043SO  2006       7          24         2006FA0000693    120060718G2910                CIRCUIT BREAKER                         PIPER PA46  PA46500TP   7104622SO                                                               COCKPIT         OPEN            B      K   NONE                                                                                            O  OTHER                                                                         DEDESCENT        1                      EA0753667                       4697158                                 DURING ROUTINE FLIGHT, GEAR WOULD NOT EXTEND UPON SELECTING GEAR LEVER DOWN. FOUND 25 AMP HYDRAULIC PUMP CIRCUIT BREAKER OPEN. RESET BREAKER AND GEAR OPERATED NORMALLY. GEAR OPERATED NORMAL FOR SEVERAL CYCLES AFTERWARD. HYDRAULIC SYSTEM WAS INSPECTED, INCLUDING CHECK FOR EXCESSIVE CURRENT DRAW WITH NO DISCREPANCY NOTED. INITIAL CURRENT DRAW ON PUMP SPIKES ABOVE THE 25 AMP LIMIT OF CB BUT IS WITHIN THE OPERATING LIMITS OF THE CB.THIS IS SECOND TIME THIS PROBLEM HAS BEEN NOTED ON THIS AIRCRAFT.  THIS SAME SCENARIO HAS BEEN NOTED ON T2 OTHER AIRCRAFT. RECOMMEND REPLACEMENT OF CB TO HIGHER CURRENT ( 30 AMPS MINIMUM). THIS MAY REQUIRE PARTIAL REWIRING OF SYSTEM DUE TO INCREASED CURRENT.                              1L71 3O    RTA25SO                        
20060724000462006072400046SO  2006       7          24         2006FA0000694    120060718G2910                CIRCUIT BREAKER                         PIPER PA46  PA46500TP   7104622SO                                                               COCKPIT         OPEN            B      K   NONE                                                                                            O  OTHER                                                                         DEDESCENT        1                      EA0753667                       4697158                                 DURING ROUTINE FLIGHT, GEAR WOULD NOT EXTEND UPON SELECTING GEAR LEVER DOWN. FOUND 25 AMP HYDRAULIC PUMP CIRCUIT BREAKER OPEN. RESET BREAKER AND GEAR OPERATED NORMALLY. GEAR OPERATED NORMAL FOR SEVERAL CYCLES AFTERWARD. HYDRAULIC SYSTEM WAS INSPECTED, INCLUDING CHECK FOR EXCESSIVE CURRENT DRAW WITH NO DISCREPANCY NOTED. INITIAL CURRENT DRAW ON PUMP SPIKES ABOVE THE 25 AMP LIMIT OF CB BUT IS WITHIN THE OPERATING LIMITS OF THE CB.THIS IS SECOND TIME THIS PROBLEM HAS BEEN NOTED ON THIS AIRCRAFT.  THIS SAME SCENARIO HAS BEEN NOTED ON TWO OTHER AIRCRAFT. RECOMMEND REPLACEMENT OF CB TO HIGHER CURRENT ( 30 AMPS MINIMUM). THIS MAY REQUIRE PARTIAL REWIRING OF SYSTEM DUE TO INCREASED CURRENT.                             1L71 3O    RTA25SO                        
20060725001962006072500196CE  2006       7          25         2006FA0000695    120060202G3040                CONNECTOR                               BEECH 200   200BEECH    1152920CE                                                               WINDSHIELD HEAT FAILED          B  HBKRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW11440WA                       BB700                                   WHILE INVESTIGATING PILOTS AND CO-PILOTS WINDSHIELD HEAT BEING INOPERATIVE, CONNECTION AT DC PWR DISTRIBUTION PNL WAS AT FAULT.  USING MFG WIRING DIAGRAM, CONNECTIONS AT JUNCT 195 AND PLUG 195 HAD BEEN SUBJECTED TO EXCESS HEATING TO POINT THAT WIRE AND WIRING INSULATION BEING BURNED AS A RESULT CONNECTIONS BEING LOOSE.  STRAIN RELIEF FOR PLUG DOES NOT ENSURE A SECURE CONNECTION FOR 8 AWG WIRE TO MAINTAIN A POS CONTACT.  END RESULT IS CONNECTIONS WORK LOOSE, BEGIN TO ARC. ARCING GENERATES HEAT. BURNING WIRE, CAUSING SOCKET CONNECTION, PIN TO BECOME BRITTLE AND WEAK.  THIS FAILURE OF CONNECTION RENDER WINDSHIELD HEAT SYS INOPERATIVE.  HEAT GENERATED FROM CONNECTION FAILURE CREATES A POTENTIAL FIRE HAZARD FOR AC. 1L72 4T      A24CE                        
20060725002442006072500244CE  2006       7          25         2006FA0000696    120060210G2497                WIRE                                    MTSBSIMU300 MU300       5780602CE  PWA   JT15  JT15D4      52112NE                                              BURNED          B  BG5YK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA33109PW                       AO46SA      PCE70800                    SHORT CIRCUIT, WIRES BURNED ON LT CNTRL JUNCT BOX AREA.  DURING SCHEDULED B INSP IAW MM, FOUND WIRES BURNED, DAMAGED ON CABLE LOOM CONNECTOR P AND J 230.  DUE TO SHORT CIRCUIT ON TRIPLE WIRES, INSULATION OF SHIELD TERM SUSPECT ON CABLES LOOM CONNECTORS.  SB MUST BE APPLIED WHICH MODIFIES SHIELDS GROUND TERM RELOCATION.  ALL WIRES AT EFFECTED CONNECTORS TO BE IDENTIFIED, CIRCUITS CHECKED IAW AC WIRING DIAGRAM, CHECKED FOR CONTINUITY, INSULATION RESIST CHECKS ON ALL WIRES NOT ONLY TO DETERMINE IF ANY OF SCREENED CABLES ARE BREAKING DOWN BUT ALSO NOT BREAKING DOWN TO ADJACENT CABLES FURTHER DOWN WIRING LOOM IN AREAS THAT CAN NOT BE VISUALLY INSP  DAMAGED WIRES REPAIRED, CONNECTORS REPLACED IAW MM.                 2H72 4F4  FRTA14SW   E1NE                 
20060725002052006072500205CE  2006       7          25         2006FA0000705    120060720G61009696001123      LINE                                    BEECH 58    58          1152740CE                                                               LT PROPELLER    CHAFED          B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP27870JA1717                   TH2036                                  LT PROPELLER ACCUMULATOR OIL LINE WAS CHAFED BY THE SHROUD FOR THE FUEL PUMP HOSE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L72 3O      3A16                         
20060725002162006072500216CE  2006       7          25         2006FA0000706    120060720G61009696001123      LINE                                    BEECH 58    58          1152740CE                                                               LT PROPELLER    CHAFED          B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP25874JE1519                   TH2045                                  LT PROPELLER ACCUMULATOR OIL LINE WAS CHAFED BY THE SHROUD FOR THE FUEL PUMP HOSE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L72 3O      3A16                         
20060725002182006072500218CE  2006       7          25         2006FA0000707    120060720G61009696001123      LINE                                    BEECH 58    58          1152740CE                                                               LT PROPELLER    CHAFED          B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP25876JK1449                   TH2053                                  LT PROPELLER ACCUMULATOR OIL LINE WAS CHAFED THROUGH BY THE SHROUD FOR THE FUEL PUMP HOSE. OIL LEAK WAS OBSERVED. THE CAUSE WAS DETERMINED AND REMEDIED BEFORE LOSS OF SIGNIFICANT AMOUNT OIL.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L72 3O      3A16                         
20060724000852006072400085SO  2006       7          24         2006FA0000710    220060720G8520                CRANKCASE       CONT        IO550B      BEECH 36    A36         1151604CE  CONT  O550  IO550B           SO                              ENGINE          CRACKED         D      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      WP258296R1320       8288849R    E2763       828849R                     ENGINE CASE CRACKED NEAR (7TH) STUD BETWEEN CYLINDERS 2 AND 4.  PROBLEM FOUND WHEN INVESTIGATING OIL LEAK.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L71 3O3  O  3A15    E3SO                 
20060803000042006080300004EU  2006       8          3          2006FA0000714    120060713G554380483205801     ATTACH FITTING                          PIAGIOP180  P180        6960204EU  PWA   PT6   PT6A6       52043EA                              RUDDER TRIM     CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO1329JS 923                    1046                                    ON POST MAINTENANCE WALKAROUND INSPECTION, FOUND RUDDER TRIM TAB LOWER CONTROL ROD ATTACH LUG RADIALLY CRACKED.  UNKNOWN CAUSE, NO OTHER DAMAGE OR DEFECTS NOTED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H72 3O3  TRTA59EU   E4EA                 
20060802001852006080200185CE  2006       8          2          2006FA0000715    120060619G3297TVA209          CAPACITOR                               BEECH 23    B24R        1151253CE                                                               GLARE SHLD FWD  EXPLODED        B  BFYSA   UNSCHED LANDING                                                                                 O  OTHER                                                                         TOTAKEOFF        1                      NE056978R                       MC324                                   OPERATOR HAD DRAWN THE BATTERY CHARGE DOWN CONSIDERABLY TRYING TO START THE AIRCRAFT.  PILOT REPORTED HEARING A POP AND REPORTED SMOKE ING CABIN.  TAKEOFF WAS ABORTED AND AN EMERGENCY (GEAR UP) LANDING WAS MADE RESULTING IN SUBSTANTIAL DAMAGE TO AC.  ON INSPECTION A CAPACITOR WAS FOUND SECURED TO THE REAR OF THE AUDIO CONTROL PANEL, THIS CAPACITOR WAS INSTALLED IN THE KN 4 CB WIRE.  CAPACITOR HAD END BLOWN OUT AND ALL ITS CONTENTS SPLATTERED ON WINSHIELD AIR DUCT.  LOW BATTERY CHARGE COUPLED WITH THE HIGH IN RUSH CURRENT DEMAND OF THE GEAR MOTOR OVER AND ABOVE THE NORMAL DEMANDS OF THE AVIONICS MOST LIKELY RESULTED IN AN OVER VOLTAGE CONDITION THAT CAUSED THE CAPACITOR TO EXPLODE.  (K)                          1L71 3O      A1CE                         
20060803000492006080300049SW  2006       8          3          2006FA0000716    120060307G2622344             EXTINGUISHER                            BELL  206   206B        1181511SW  ALLSN 250C  250C30      03013GL                              COCKPIT         EXPLODED        D  I22FO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO23615LH                       2263                                    A NEW 1.25 LB EXTINGUISHER MODEL 344, SN W-968052 CLASSIFICATION 2-B; C WAS INSTALLED IN THE AIRCRAFT ON MARCH 6, 2006.  IT WAS REMOVED OVERNIGHT AND REINSTALLED AT 8:50 AM ON MARCH 7, 2006.  AS THE HELICOPTER WAS STARTING, THE END EXPLODED OUT OF THE EXTINGUISHER, FIRING IT INTO THE CONSOLE.  THE TEMPERATURE IN THE COCKPIT WAS APPROXIMATELY 36 DEGREES C AND THE EXTINGUISHER WAS IN THE SHADE.  THE PRESSURE GAUGE WAS IN THE GREEN WHEN INSTALLED.  (K)                                                                                                                                                                                                                                                                           1G71 3U3  U  H2SW    E1GL                 
20060803000082006080300008SO  2006       8          3          2006FA0000717    120060311G5712                RIB                                     PIPER PA34  PA34220T    7103420SO  CONT  O360  TSIO360*    17025SO                              LEFT & RIGHT    CRACKED         B  Q2ARK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW178164D5963                   348233086                               DURING COMPLIANCE WITH SB, LT AND RT RIBS FOUND CRACKED AS SUSPECTED.  INSTALLED REPAIR KITS.  LT DRAG BRACE PIVOT, PN 39479002, ALSO FOUND CORRODED AND CRACKED.  THIS IS NOT PART OF SB INSPECTION.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L72 3O3  O  A7SO    E9CE                 
20060803001032006080300103    2006       8          3          2006FA0000718    420060713G2562DMELT6          ELT                                     CESSNA210   T210N       2073456CE                                                               CABIN           INOPERATIVE     B  GFVRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM13178JD                       21063351                                FOUND ELT TOTALLY INOPERATIVE DURING ANNUAL INSPECTION, BATTERY VOLTAGE OK.  UNABLE TO DETERMINE IF IMPACT SWITCH WAS ALSO INOPERATIVE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H71 3O      3A21                         
20060803000102006080300010SO  2006       8          3          2006FA0000719    220060601G8530                EXHAUST VALVE                           CESSNA337   337B        2075706CE  CONT  O360  IO360CONT   17025SO                              NR 6 CYLINDER   STUCK           D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA212362S                       3370662                                 ENGINE RUNNING ROUGH.  COLD COMPRESSION CHECK SHOWED -0- COMPRESSION ON NR 6 CYLINDER.  AIR LEAKING PAST EXHAUST VALVE.  DISASSEMBLY REVEALED EXHAUST VALVE STUCK IN OPEN POSITION.  EVIDENCE OF PISTON STICKING EXHAUST VALVE.  THIS IS THE SECOND OCCURANCE OF THIS CONDITION ON THIS ENGINE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                            1H72 3O3  O  A6CE    E1CE                 
20060803000452006080300045SO  2006       8          3          2006FA0000720    220060515G8530                EXHAUST VALVE                           CESSNA337   337B        2075706CE  CONT  O360  IO360CONT   17025SO                              NR 4            STUCK           D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA212362S275        AC05AC028   3370662                                 ENGINE RUNNING ROUGH.  PERFORMED COLD COMPRESSION CHECK.  COMPRESSION WAS ZERO.  AIR LOOKING PAST EXHAUST VALVE.  REMOVED ROCKER ARM COVER, NOTED EXHAUST VALVE STICKING IN OPEN POSITION.  REMOVED CYLINDER.  PISTON HAD STRUCK EXHAUST VALVE.  REPLACED CYLINDER AND PISTON.  PISTON WAS DIFFERENT THAN ORIGINAL PN WAS  THE SAME, TOP OF PISTON WAS CONCAVE WHERE AS ORIGINAL PISTON WAS FLAT.  (K)                                                                                                                                                                                                                                                                                                                                          1H72 3O3  O  A6CE    E1CE                 
20060802002762006080200276CE  2006       8          2          2006FA0000721    120060619G25205514551169      SEAT                                    CESSNA501   501         2076603CE                                                               CABIN           CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE05501CF                       5010128                                 UPPER CHAIR BASE ASSEMBLY CRACKED AT CHAIR BACK ATTACH POINTS.  ALSO, PREVIOUS INAPPROPRIATE REPAIR.  CHAIR WAS REPAIRED IAW STC, STRUCTURAL SEAT REPAIR.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L72 4F      A27CE                        
20060803000502006080300050    2006       8          3          2006FA0000722    220060725G74143975            MAGNETO                                                                                                                                 ENGINE          OUT OF TOLERANCEB  S4CRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP25                                                                    OUT OF TOLERANCE SECONDARY WINDINGS FOUND ON MAGNETO COIL. READINGS INDICATED VERY LOW RESISTANCE, WHICH FLUCTUATED WITH AMBIENT TEMPERATURE CHANGES. NORMAL READINGS FALL CLOSE TO 15,000 OHMS, WHEREAS THIS FAULTY COIL READ BETWEEN 2,000 OHMS, UP TO 5,000 OHMS. 13,000 OHMS IS DESCRIBED AS THE LOWEST READING ALLOWED BY THE MANUFACTURER OF THIS MAGNETO. THIS ISSUE WAS DISCOVERED DURING PREVENTIVE MAINTENANCE, WHICH INCLUDED INSPECTION OF MAGNETO INTERNALS. THE SN DATE CODE SUGGESTS THAT THIS MAGNETO WAS MANUFACTURED IN 1992.                                                                                                                                                                                                                                           
20060803000992006080300099    2006       8          3          2006FA0000723    220060725G74143975            COIL            SLICK                                                                                                                   MAGNETO         OUT OF TOLERANCEB  S4CRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP25                92120190                                            OUT OF TOLERANCE SECONDARY WINDINGS FOUND ON MAGNETO COIL. READINGS INDICATED VERY LOW RESISTANCE, WHICH FLUCTUATED WITH AMBIENT TEMPERATURE CHANGES. NORMAL READINGS FALL CLOSE TO 15,000 OHMS, WHEREAS THIS FAULTY COIL READ BETWEEN 2,000 OHMS, UP TO 5,000 OHMS. 13,000 OHMS IS DESCRIBED AS THE LOWEST READING ALLOWED BY THE MANUFACTURER OF THIS MAGNETO. THIS ISSUE WAS DISCOVERED DURING PREVENTIVE MAINTENANCE, WHICH INCLUDED INSPECTION OF MAGNETO INTERNALS. THE SERIAL NUMBER DATE CODE SUGGESTS THAT THIS MAGNETO WAS MANUFACTURED IN 1992.                                                                                                                                                                                                                                
20060803001012006080300101    2006       8          3          2006FA0000724    220060725G74143975            COIL            SLICK                                                                                                                   MAGNETO         OUT OF TOLERANCEB      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP25                92120190                                            OUT OF TOLERANCE SECONDARY WINDINGS FOUND ON MAGNETO COIL. READINGS INDICATED VERY LOW RESISTANCE, WHICH FLUCTUATED WITH AMBIENT TEMPERATURE CHANGES. NORMAL READINGS FALL CLOSE TO 15,000 OHMS, WHEREAS THIS FAULTY COIL READ BETWEEN 2,000 OHMS, UP TO 5,000 OHMS. 13,000 OHMS IS DESCRIBED AS THE LOWEST READING ALLOWED BY THE MANUFACTURER OF THIS MAGNETO. THIS ISSUE WAS DISCOVERED DURING PREVENTIVE MAINTENANCE, WHICH INCLUDED INSPECTION OF MAGNETO INTERNALS. THE SERIAL NUMBER DATE CODE SUGGESTS THAT THIS MAGNETO WAS MANUFACTURED IN 1992. THANK YOU.                                                                                                                                                                                                                     
20060802000532006080200053CE  2006       8          2          2006FA0000725    120060711G27100510105365      CONTROL CABLE                           CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              AILERON         FRAYED          B  7TFRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP072134M2164                   172S9552                                DURING AN ANNUAL INSPECTION OF THE RT WING, THE AILERON CROSSOVER CABLE WAS FOUND TO BE FRAYED AT THE WEAR BLOCK.  PROBABLE CAUSE IS THAT THE WEAR BLOCK IS CAUSING FRICTION AND WEAR ON THE CABLE.  A RECOMMENDED SOLUTION IS TO REMOVE THE WEAR BLOCK.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3O3  ONT3A12    1E10                 
20060802001812006080200181SO  2006       8          2          2006FA0000726    120060720G3230                DRAG LINK                               PIPER PA23  PA23160     7102304SO  LYC   O320  O320*       41508EA                              RT MLG          FAILED          G      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW054233P                       231730                                  DURING THE INVESTIGATION, IT WAS DISCOVERED THAT THE RT MLG UPPER DRAG LINK ASSY HAD FAILED AT THE ATTACHMENT POINT FOR THE MLG DOWNLOCK LATCH ASSY.  A VISUAL INSPECTION OF THE BROKEN DRAG LINK SHOWED THAT THE ASSY HAD A METAL FATIGUE CRACK ALONG THE CIRCUMFERENCE OF THE COMPONENT.  THE CRACKED AREAS SHOWED EVIDENCE OF CORROSION THAT APPEARS TO HAVE BEEN THERE FOR A LONG PERIORD OF TIME.  (K)                                                                                                                                                                                                                                                                                                                                     1L72 3O3  O  1A10    E274                 
20060803000032006080300003CE  2006       8          3          2006FA0000727    120060714G280007600261        GUARD                                   CESSNA182   T182T       2072738CE  LYC   O540  TIO540*     41532EA                              FUEL SYSTEM     OUT OF RIG      C  GFVRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM131568W                       T18208394                               PROTECTIVE GUARDS ARE CALLED OUT BY IPL ORIGINALLY, IPL REV 7 DOES, REV 8 DOES NOT.  CURRENT REVISION 12, CALLS FOR THE GUARDS TO BE INSTALLED REV 13 IS IN TRANSIT BUT SHOULD INCLUDE THE CALL OUT.  THIS AIRCRAFT HAS INDICATIONS THAT ELEVATOR CONTROL LINES HAVE MADE LIGHT CONTACT WITH FUEL LINES.  BUT THERE IS NO DAMAGE.  PARTS ORDERED.  AIRCRAFT TT 159 HOURS (FIRST ANNUAL INSPECTION).  (K)                                                                                                                                                                                                                                                                                                                                        1H71 3O3  ONT3A13    E14EA                
20060803000052006080300005NM  2006       8          3          2006FA0000728    120060703G2910AE70577756      HOSE                                    BOEING757   7572Q8      1384972NM                                                               HYDRAULIC SYSTEMMISINSTALLED    B  LH6YK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA35719BC                       25131                                   NR 1 ENGINE HYDRAULIC PUMP SUCTION/SUPPLY DISCONNECT.  DURING THE REPLACEMENT OF NR 1, ENGINE EDP DUE TO NO OFFLOAD, IT NOTED THAT THE SUPPLY DISCONNECT WAS FITTED WITH THE PUMP UNION AT THE WRONG END OF THE DISCONNECT, AND ON REMOVAL IT WAS NOTED THAT THE INTERVAL S/OFF MECHANISM HAD BEEN REMOVED.  THE VALVE, UNION AND SEALS WERE SUBSEQUENTLY REPLACED.  (K)                                                                                                                                                                                                                                                                                                                                                                        2L72 4F    RTA2NM                         
20060803000072006080300007EA  2006       8          3          2006FA0000729    220060714G8550                ADAPTER                                 ROBSINR22   R22BETA     7640110NM  LYC   O320  O320B2C     41508EA                              ENGINE          BROKEN          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM08185MH                       0976                                    WHILE CHANGING OIL FILTER DURING ROUTINE 100 HR INSPECTION, OIL FILTER ADAPTER CENTER THREADED SHAFT BROKE OFF LEAVING HALF SHAFT INSIDE ADAPTER AND OTHER HALF THREADED INTO OIL FILTER.  THIS OCCURRED WITH MINIMAL ROTATIONAL TORQUE BEING APPLIED.  INSPECTION OF SHAFT REVEALED THAT MACHINED CENTER SECTION OF SHAFT AT SHEAR POINT WAS MACHINED TO DEEP LEAVING ONLY A MAXIMUM WALL THICKNESS OF .020, AND PROBABLY MUCH LESS AT SHEAR LINE JUDGING BY KNIFE EDGE CONDITION OF BREAK POINT.  RECOMMENDATION: FURTHER INVESTIGATION AT MFG LEVEL POSSIBLE AD GENERATION TO DETERMINE IF OTHER UNITS CURRENTLY IN SERVICE HAVE SAME DEFECT CONDITION.                                                                                      1G71 3O3  O  H10WE   E274                 
20060802002972006080200297CE  2006       8          2          2006FA0000730    120060702G49403046342         IGNITER                                 LEAR  45    45LEAR      5170805CE  GARRTTTFE731TFE731*     01518WP                              APU             SEPARATED       D      O   OTHER                                                                                           O  OTHER                                                                         ININSP/MAINT     1                      SW99826CA                       222                                     PART OF IGNITER PLUG THAT SURROUNDS ELECTRODE SEPARATES AND SHORTS AGAINST THE ELECTRODE CAUSING THE APU NOT TO START.  PART COULD POSSIBLY ENTER THE COMBUSTION AREA OF THE APU.  (NOTE: APU HAS ONE IGNITER,  HAD 2 RECENT FAILURES).                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRTT00008WIE6WE                 
20060803000932006080300093CE  2006       8          3          2006FA0000731    120060702G49403046342         IGNITER                                 LEAR  45    45LEAR      5170805CE  GARRTTTFE731TFE73160         NE                              APU             BROKEN          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW99882CA792                    155                                     PART OF IGNITER PLUG THAT SURROUNDS ELECTRODE SEPARATES AND SHORTS AGAINST THE ELECTRODE CAUSING THE APU NOT TO START.  PART COULD POSSIBLY ENTER THE COMBUSTION AREA OF THE APU.  (NOTE: APU HAS ONE IGNITER, WE HAVE HAD 2 RECENT FAILURES).  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F4  FRTT00008WIE1NM                 
20060808000802006080800080GL  2006       8          8          2006FA0000732    320060714G6110ACA1373         NUT                                                                                                         HARTZLHCB4M HCB4M       GL  CLAMP           FAILED          B  JGVRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09                                                    FWA2178         WHEN TORQUING OUTER CLAMP NUT PN ACA1373, NEW OUTER CLAMP NUT THREADS FAILED BEFORE REACHING SPECIFIED TORQUE.  PROPELLER WAS BEING REASSEMBLED DURING OVERHAUL.  ASSEMBLED USING CALIBRATED TOOLS AND NEW HARDWARE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    6  CP56GL    
20060803000942006080300094EU  2006       8          3          2006FA0000733    220060607G72409387M34G01      TUBE                                    BOEING737   737300      1384610NM  CFMINTCFM56 CFM563B2    13802EU                              FUEL DRAIN      DAMAGED         C  QEMYK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA35GLGTG           41X24410                                            (REF: MDR NR MDR002/06)  STRIP OF CORE ASSEMBLY NOTED FRETTAGE DAMAGE TO 3 LOCATIONS ON THE NR 3 POSITION FUEL NOZZLE DRAIN TUBE.  THE DEEPEST WAS TO A DEPTH OF .016 INCH.  THE ROUTE CAUSE OF THE FRETTAGE HAD BEEN DETERMINED AS CONTACT WITH RIVETS ON THE DEFLECTOR ASSY.  THE MODULE (41X24410) WAS REFURBISHED IAW BA REFURBISH SPECIFICATION AND IAW 72-41-XX AT LAST SHOP VISIT.  (K)                                                                                                                                                                                                                                                                                                                                                  2L72 4F4  FRTA16WE   E21EU                
20060829000842006082900084CE  2006       8          29         2006FA0000734    120060727G3230                LANDING GEAR                            BEECH 35    A35         1151504CE  CONT  E185  E185*       17014SO                              NLG             COLLAPSED       C      K   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      GL05417TZ                       D2053                                   NOSE GEAR COLLAPSED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L71 3O3  O  A777    E246                 
20060803000512006080300051SO  2006       8          3          2006FA0000735    120060726G2432                CAPACITOR       ELDEC                   GULSTMGV    GULFSTREAMGV3980116SO                                                               BATTERY CHARGER BURNED          C      H   DEACTIVATE SYST/CIRCUITS                                                                        A  FLAME/FIRE                                                                    LDLANDING        1                      EA07410LM2996       B317        578                                     AFTER LANDING AIRCRAFT TAXIED TO HANGAR. WHEN AIRCRAFT STOPPED GROUND CREW NOTICED SMOKE COMING FROM TAIL COMPARTMENT. INVESTIGATION FOUND SMOKE AND FLAMES COMING FROM RT BATTERY CHARGER. ELECTRICAL POWER REMOVED FROM AIRCRAFT. FLAMES SELF EXTINGUISHED AND CHARGER WAS THEN REMOVED FROM AIRCRAFT. NO DAMAGE TO SURROUNDING AIRCRAFT STRUCTURE. REPLACEMENT CHARGER INSTALLED OPS CHECK OK.                                                                                                                                                                                                                                                                                                                                               2L72 4F    RTA12EA                        
20060816003072006081600307GL  2006       8          16         2006FA0000736    220060525G8530                CYLINDER HEAD                           MTSBSIMU2   MU2B20      5780407SW  HIRTH 2706  2706*            GL                              ENGINE          STRIPPED        G      B   EMER. DESCENT                                                                                   O  OTHER                                                                         TOTAKEOFF        1                      WP09555C                        129         A882299                     NOTE: THIS AIRCRAFT WAS BUILT UNDER FAA EXPERIMENTAL AMATURE BUILT GUIDANCE. THIS AIRCRAFT IS NOT A LIGHT SPORT AIRCRAFT. IT WAS BUILT FROM A KIT AND CERTIFIED AS AN EXPERIMENTAL AMATURE BUILT AIRCRAFT.  LOST ENGINE POWER AFTER TAKE-OFF AND MADE EMERGENCY LANDING WITH EXPERIMENTAL AMATURE BUILT AIRCRAFT: (HORNET)DETAILS: 2 CYLINDER,2 CYCLE ENGINE. 2 SPARK PLUGS IN EACH CYLINDER.  AFT SPARK PLUG SEPARATED FROM AFT CYLINDER. THREADS THAT WERE MILLED INTO CYLINDER HEAD FAILED TO HOLD SPARK PLUG CAUSING DEPARTURE OF PLUG, LOSS OF COMPRESSION AND POWER LOSS CAUSING AN EMERGENCY LANDING. REPAIR WAS MADE BY INSTALLING A HELI-COIL INTO CYLINDER HEAD & REINSTALLING A SPARK PLUG.                                          1H72 3T3  I  A2PC    EXPE3I               
20060814001212006081400121SO  2006       8          14         2006FA0000740    120060804G78103022406         EXHAUST DUCT                            GRUMAVG21   G21A        3951204SO  PWA   PT6   PT6A41      52043EA                              LT ENGINE       CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO092293216012660               B139        PCE81118                    EXHAUST DUCT ASSY CRACKED AND MISSING PARTS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H72 3R4  T  TC654   E4EA                 
20060808000732006080800073NM  2006       8          8          2006FA0000741    120060626G2497                WIRE            TRW                     DHAV  DHC8  DHC8*              NM                                                               AC GENERATOR    BROKEN          B  VNNRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA65                799                                                 EXCITER ROTOR LEADWIRE BROKEN AT SOLDER CONNECTION TO DIODE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2H72 4T    RTA13NM                        
20060808000762006080800076NM  2006       8          8          2006FA0000742    120060706G2497                WIRE            TRW                     DHAV  DHC8  DHC8*              NM                                                               AC GENERATOR    BROKEN          B  VNNRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA65          2415  1163                                                EXCITER ROTOR LEAD WIRES BROKEN AT DIODE CONNECTION WIRES WERE INCORRECTLY SOLDERED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2H72 4T    RTA13NM                        
20060808000742006080800074NM  2006       8          8          2006FA0000743    120060706G249731708301        WIRE                                    DHAV  DHC8  DHC8*              NM                                                               AC GENERATOR    BROKEN          B  VNNRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA65          2476                                                      EXCITER ROTOR LEAD WIRES BROKEN AT CONNECTION TO DIODE. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2H72 4T    RTA13NM                        
20060808000842006080800084NM  2006       8          8          2006FA0000744    120060706G2497                WIRE            TRW                     DHAV  DHC8  DHC8*              NM                                                               AC GENERATOR    BROKEN          B  VNNRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA65                654                                                 EXCITER ROTOR LEAD WIRES BROKEN AT CONNECTION TO DIODES, INCORRECTLY SOLDERED TO DIODE. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2H72 4T    RTA13NM                        
20060808000772006080800077NM  2006       8          8          2006FA0000745    120060706G2497                WIRE            TRW                     DHAV  DHC8  DHC8*              NM                                                               AC GENERATOR    BROKEN          B  VNNRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA65          9658  1188                                                EXCITER ROTOR LEAD WIRES BROKEN AT CONNECTION BETWEEN DIODE AND RESISTOR.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2H72 4T    RTA13NM                        
20060810001182006081000118EA  2006       8          10         2006FA0000747    220060717G7310050011842       FUEL LINE                               CESSNA172   172K        2072430CE  LYC   O320  O320*       41508EA                              ENGINE          CHAFED          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP0979130                       17257901                                DURING AN ANNUAL INSPECTION, BOTH ENGINE FUEL SUPPLY LINES WERE FOUND TO BE CHAFFING THE FWD BULKHEAD OF THE LANDING GEAR BOX STRUCTURE AT BS 56.70.  MDG HAS INSTALLED A THIN PLASTIC SLEEVE OVER THE LINES IN THE AREA OF THE CHAFE BUT, AFTER 2564 HOURS, THE SLEEVE IS CHAFFED TOT HE EXTENT THAT THE TUBES WILL NO LONGER BE PROTECTED.  FEEL THAT THE TUBE INTEGRITY WOULD BE COMPROMISED IN THE FUTURE.  ADDITIONAL CHAFE PROTECTION AND LINE SECURING IS REQUIRED.  ILLUSTRATION SHOWS A HEAVIER CHAFE BARRIER INSTALLED ON THE TUBES IN THE AREA NOTED ABOVE.  SUGGEST BONDING A LENGTH OF MIL .3750 INCH ID TUBING  OVER THE MFG LINE IN THE CHAFE ARREARS.  ADDITIONAL ADJUSTMENT OF THE EXISTING LINE CLAMPS MAY ALSO BE REQUIRED.  1H71 3O3  ONT3A12    E274                 
20060810001162006081000116SO  2006       8          10         2006FA0000748    120060407G27206282905         SHAFT                                   PIPER PA32  PA32300     7103212SO  LYC   O540  IO540*      41532EA                              RUDDER          MISREPAIRED     C  NT2RK   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CE07195PJ                       327840092                               RUDDER TRIM BUNGEE SHAFT ASSY PN 6282905, HAD BEEN IMPROPERLY REPAIRED BY PERSONS UNKNOWN CAUSING BUNGEE TO BOTTOM OUT WHEN RUDDER PEDAL DEFLECTED TO LIMIT WHICH IN TURN CAUSED UNDO PRESSURE ON RUDDER CONTROL  ARM, PN 6345703, EVENTUALLY CAUSING ARM TO BREAK.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L71 3O3  O  A3SO    1E4                  
20060810001172006081000117EA  2006       8          10         2006FA0000749    220060720G8530LW14995         SPRING          LYC                     SOCATATB20  TB21        8680697EU  LYC   O540  TIO540AB1A  41533EA                              CYLINDER        BROKEN          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE072802W232                    1137        L921061A                    THE PUSH ROD HOUSING TUBE RETAINING SPRINGS WERE BROKEN AT THE BEND JUST OB OF THE MOUNT HOLE.  THE UNBROKEN SPRINGS HAD A TOOL LINE AT THE POINT OF THE BEND.  THERE WERE 2 BROKEN SPRINGS, LOCATED ON NR 3 AND NR 4 CYLINDERS.  ONE SPRING HAD ONE SIDE BROKEN OFF THE OTHER BOTH SIDES WERE BROKEN.  BELIEVE THE TOOL MARKS ARE CAUSING THE PROBLEM.  ALL 6 SPRINGS WERE REPLACED WITH NEW MFG PARTS AND SOME ALSO CONTAINED THE TOOL MARKS AT THE BEND.  (K)                                                                                                                                                                                                                                                                                1L71 3O3  ORTA51EU   E14EA                
20060810001302006081000130CE  2006       8          10         2006FA0000750    120060604G323398820152        HOUSING                                 CESSNA172   172RG       2072438CE  LYC   O360  O360F1A6    41514EA  MCAULY2D34C B2D34C220   GL  ACTUATOR        CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP099394D                       172RG1150   L3758836A   796893          RT MAINT GEAR ACTUATOR HOUSING CRACKED THROUGH THE BOLT HOLES OF CASTING , CAUSING  RACK TO DISENGAGE FROM PIVOT GEAR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3O3  O  3A17    E286    5  CP7EA     
20060810001212006081000121EU  2006       8          10         2006FA0000751    120060713G6220350A310033KIT7  SPRING                                  SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1        NE                              VIBRATION ABSORBBROKEN          B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA17461SA2130       M2026       3605                                    PILOT REPORTED EXCESSIVE CABIN VIBRATION AT FULL POWER WHILE ON THE GROUND.  VIBRATION SUBSIDED IN A HOUR AND THROUGHOUT THE FLIGHT ENVELOPE.  DISASSEMBLY AND INSPECTION REVEALED 1 OF 3 SPRINGS IN VIBRATION ABSORBER OF MAIN ROTOR CRACKED ALL THE WAY THROUGH.  COMPLIED WITH 2500 HR INSPECTION OF VIBRATION ABSORBER JAW MFG MAINT WORK CARDS AND SERVICING RECORDS.  REPLACED ALL 3 SPRINGS AND PN EN2023R12L.  BEARINGS WHICH HAD EXCESSIVE PLAY.  REINSTALLED AN AIRCRAFT AND VIBRATION WAS ELIMINATED.  (K)                                                                                                                                                                                                                           1G71 3U3  U  H9EU    E19EU                
20060810001122006081000112GL  2006       8          10         2006FA0000752    120060720G7120                SAFETY WIRE                             AMTR  LANCARLC41550FG   5150001GL                                                               NR 4 ENG MOUNT  MISINSTALLED    C      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      SW072542T391                    41508                                   ALL 4 ENGINE VIBRATION ISOLATOR MOUNT BOLTS WERE SAFETY WIRED BACKWARDS.  NO EVIDENCE OF DAMAGE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L71 3O    RTEXPA1L71                     
20060810001232006081000123CE  2006       8          10         2006FA0000753    120060718G5540081301316       TORQUE TUBE                             CESSNA310   310Q        2074242CE                                                               RUDDER          DAMAGED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03119RS                       310Q0906                                RT RUDDER TORQUE TUBE RIPPED AT RUDDER CABLE BRACKET.  INSPECT THIS AREA NEXT TO WELD.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L72 3O      3A10                         
20060810001382006081000138SO  2006       8          10         2006FA0000755    120060731G8011                RING GEAR                               PIPER PA31  PA31350     7103110SO  LYC   O540  TIO540N2BD  41532EA                              STARTER         FAILED          B  EVTRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO333542D291        E052921     317952232   L1000961A                   TRIED TO START ENGINE WOULD NOT START VISUAL BENDIX TO RING GEAR TEETH IN BOTTOM OF STARTER HOUSING.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 3O3  O  A20SO   E14EA                
20060810001272006081000127SW  2006       8          10         2006FA0000756    120060721G2497112             WIRE                                    BBAVIA7     7ECA        21101NNSW  LYC   O235  O235*       41505EA                              FIREWALL        SHORTED         D      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      NE018750V1568                   110475                                  WHILE IN FLIGHT, THE PILOT REPORTED HE COULD SMELL SOMETHING BURNING, LANDED AS SOON AS PRACTICAL.  INVESTIGATION REVEALED THAT THE WIRE FROM THE ALTERNATOR TO THE AMMETER, PN 112 HAD SHORTED AGAINST THE FIREWALL, WHERE IR GOES THROUGH THE FIRE WALL.  WIRES 112, 114, MASTER RELAY, STARTER RELAY, AMMETER, VOLTAGE REGULATOR AND ALTERNATOR WERE ALL REPLACED.  (K)                                                                                                                                                                                                                                                                                                                                                                      1H71 3O3  O  A759    E223                 
20060810001362006081000136    2006       8          10         2006FA0000757    420060804G2562AK450           ELT                                     CESSNA150   150K        2071822CE  CONT  O200  O200*       17020SO                              CABIN           INOPERATIVE     C  BI1RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA055896G                       15071396                                THIS IS ONE OF THE ELT`S THAT USES DATED FLASHLIGHT BATTERIES.  THE BATTERIES ARE STILL IN DATE BUT OFTEN WE FIND THAT THE BATTERIES ARE LEAKING OR DEAD BEFORE THE EXPIRATION DATE.  RECOMMEND THAT THE BATTERIES ARE CHANGED AT EACH ANNUAL TO CORRECT THIS PROBLEM.  BATTERIES ARE CHEAP ENOUGH.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                        1H71 3O3  O  3A19    E252                 
20060814000712006081400071EA  2006       8          14         2006FA0000758    220060725G8530TISN12OCA       CYLINDER HEAD                           PIPER PA25  PA25        7102502SO  LYC   O360  O360C2A     41514EA                              RT ENGINE       SEPARATED       D      A   UNSCHED LANDING                                                                                 R  PARTIAL RPM/PWR LOSS                                                          CRCRUISE         1                      EA176471Z410                    25673       L2925936A                   THIS WAS A NEW CYLINDER INSTALLED APRIL 05, AT ENGINE OVERHAUL.  THE CYLINDER COMPLETELY SEPARATED BETWEEN THE HEAD AND BARREL, IN FLIGHT.  THE AIRCRAFT WAS SAFELY LANDED AT HOME AIRPORT.  PN STAMPED ON CLY BASE: AEL65102, SN12.0F.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L71 3O3  O  2A10    E286                 
20060810001192006081000119EA  2006       8          10         2006FA0000759    220060802G741410357281L       CAPACITOR       LYC                     BELL  47    47G4A       1181031SW  LYC   O540  VO540B1B3   41532EA                              MAGNETO         FAILED          D      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      WP171354X           1012162     7537        L174243                     LOADED HELICOPTER SAFELY LANDED AFTER MAGNETO FAILURE.  WIRE FROM CAPACITOR TO POINTS OPEN WITHIN INSULATION.  NO VISIBLE DAMAGE, HOWEVER, MOVEMENT OF WIRE AGAINST CAPACITOR RESTORES CONTACT.  YOU CAN FEEL IT.  OPEN LOCATED WHERE WIRE ENTERS CAPACITOR.  NO RECOMMENDATIONS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                          1G71 3O3  O  2H3     E304                 
20060810001322006081000132GL  2006       8          10         2006FA0000760    320060802G6111                SNAP RING                               CESSNA210   210M        2073450CE  CONT  O520  IO520*      17032SO  MCAULYD3A34 D3A34C404   GL  PROP BLADES     FAILED          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO07965B 2976 1066              21061580    295027R     782194          2 SNAP RINGS FAILED ON PROPELLAR BLADES.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3O3  O  3A21    E5CE    5  CP47GL    
20060810001142006081000114CE  2006       8          10         2006FA0000761    120060802G3297110230102       CIRCUIT BREAKER                         CESSNA177   177RG       2073709CE  LYC   O360  IO360A1B6   41514EA  MCAULY2D34C B2D34C207   GL  MLG             MALFUNCTIONED   C      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA2321EB 7567                   177RG0589   L1265751A   752186          LANDING GEAR CIRCUIT BREAKER MALFUNCTIONED.  AIRCRAFT WAS JACKED AND GEAR CYCLED SEVERAL TIMES.  COULD NOT GET THE CIRCUIT BREAKER TO MALFUNCTION ON JACKS.  RECOMMEND THAT CIRCUIT BREAKER BE REPLACED WITH NEW.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3O3  O  A20CE   1E10    5  CP7EA     
20060810001152006081000115EA  2006       8          10         2006FA0000762    220060520G8520MIOP            CRANKSHAFT                              AMTR  SISU  SISU1A      0780132GL  LYC   O360  IO360A1A    41514EA                              ENGINE          SEPARATED       D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL27818SH                       1017S1S     L1479051A                   CRANKSHAFT FLANGE SEPARATED FROM CRANK AT THE LIGHTENING HOLES. AVOID GYROSCOPIC AEROBATICS USING A CRANKSHAFT FLANGE WITH LIGHTENING HOLES.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1K00   3  ORCEXPA1K001E10                 
20060814000822006081400082    2006       8          14         2006FA0000764    220060701G8530AEL65102        CYLINDER HEAD                           PIPER PA18  PA18A       7101804SO                                                               ENGINE          SEPARATED       B  OF1RO   OTHER                                                                                           J  WARNING INDICATION                                                            CRCRUISE         1                      EA173885Z413                    187700                                  DURING NORMAL CRUISE FLIGHT, PILOT EXPERIENCED ENGINE ROUGHNESS AND A LOSS OF ENGINE OIL OUT OF THE SIDE COWLING, CAUSING AN UNEVENTFUL OFF AIRPORT LANDING.  ROUGHNESS AND OIL LOSS WERE DUE TO NR 3 CYL HEAD SEPARATING FROM THE CYLINDER BARREL AT THE 3RD COOLING FIN FROM BOTTOM OF THE HEAD.  ALTHOUGH THIS CYLINDER ECI PN IS SAME PN LISTED IN AD, THIS WAS TITAN STYLE CYL, NOT CLASSIC CAST AS INDICATED BY NR CAST INTO CYL HEAD.  THESE LATER TITAN CYL UNAFFECTED BY AD, MAY BE EXPERIENCING SAME FAILURES THAT THE EARLIER CAST CYL THAT ARE AFFECTED BY AD WERE EXPERIENCING.  (K)                                                                                                                                               1H71 3O      1A2                          
20060814001252006081400125SO  2006       8          14         2006FA0000765    120060808G321167042013        TRUNNION                                PIPER PA44  PA44180     7104402SO                                                               MLG             CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP07571ER3394                   4496147                                 DURING MAINTENANCE INSPECTION OF THE GEAR, THE MECHANIC FOUND THE AFT MAIN GEAR TRUNNION CRACKED.  DYE PENETRANT CONFIRMED CRACK.  CAUSE IS UNDETERMINED BUT THE AIRCRAFT IS USED FOR FLIGHT TRAINING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L72 3O      A19S0                        
20060814001342006081400134    2006       8          14         2006FA0000766    420060731G3497311601          WIRE HARNESS                            CESSNA650   650         2076802CE                                                                               DAMAGED         C      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      GL1396MT                        6507065                                 DUAL TRANSPONDER FAILURE IN HEAVY PRECIPITATION. NO FAILURE INDICATION ON SPZ8000 SYSTEM.  CENTER REQUESTED RESET OF TRANSPONDER, AND DIRECTED OUT OF RVSM AIRSPACE WHEN UNSUCCESSFUL.  HANGAR TESTS OF POWER OUTPUT SHOWED 40WATTS BEFORE CABLES REPLACED, AND 400 WATTS AFTER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F      A9NM                         
20060814001352006081400135    2006       8          14         2006FA0000767    420060731G3497311601          WIRE HARNESS                            CESSNA650   650         2076802CE                                                                               DAMAGED         C      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      GL1396MT                        6507065                                 DUAL TRANSPONDER FAILURE IN HEAVY PRECIPITATION. NO FAILURE INDICATION ON SPZ8000 SYSTEM.  CENTER REQUESTED RESET OF TRANSPONDER, AND DIRECTED OUT OF RVSM AIRSPACE WHEN UNSUCCESSFUL. HANGAR TESTS OF POWER OUTPUT SHOWED 40WATTS BEFORE CABLES REPLACED, AND 400 WATTS AFTER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F      A9NM                         
20060821000552006082100055    2006       8          21         2006FA0000768    420060813G3416                ALTIMETER                               BOEING777   777         UTILUSENM                                                                               INOPERATIVE     C      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW99                                                                    CAPTAIN ALTIMETER INOPERATIVE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F    RTT00001SE                     
20060814001472006081400147EA  2006       8          14         2006FA0000769    220060320G73101560016D0155    HOSE                                    CESSNA182   R182        2072734CE  LYC   O540  O540J3C5    41532EA                              FUEL SYSTEM     LEAKING         D      K   NONE                                                                                            KK FLUID LOSS                FLUID LOSS                                          ININSP/MAINT     1                      SW153648C1177                   R18200294   L2047940A                   DURING AN ANNUAL INSPECTION THE HOSE ASSEMBLY FROM THE ELECTRIC PUMP TO THE ENGINE DRIVEN FUEL PUMP WAS FOUND TO BE LEAKING.  HOSE WAS INSTALLED 5-12-03 AND REMOVED 3-20-06.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3O3  ORT3A13    E295                 
20060814001952006081400195EA  2006       8          14         2006FA0000770    220060320G7310AE3663819B0190  HOSE                                    CESSNA182   R182        2072734CE  LYC   O540  O540J3C5    41532EA                              FUEL SYS        LEAKING         D      K   NONE                                                                                            KJ FLUID LOSS                WARNING INDICATION                                  ININSP/MAINT     1                      SW153648C1177                   R18200294   L2047940A                   DURING AN ANNUAL INSPECTION THE HOSE ASSEMBLY FROM THE TEE FITTING AT CARBURETOR TO THE FIREWALL FITTING FOR FUEL PSI WAS FOUND TO BE LEAKING.  HOSE WAS INSTALLED 5-12-03.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1H71 3O3  ORT3A13    E295                 
20060817001722006081700172GL  2006       8          17         2006FA0000772    220060731G7200                COUPLING                                                                   ALLSN 250C  250C30P     03013GL                              ENGINE          FAILED          B  A9URO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW05                                        CAT90607                    NR 2 COUPLING FAILURE, WHICH CAUSED A NI FAILURE, AND INNER SHAFT FAILURE, POWER TURBINE ROTOR DECOUPLING AND GAS PRODUCER OVERTEMP.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              3  U          E1GL                 
20060814001932006081400193SO  2006       8          14         2006FA0000773    120060806G3222                SPRING                                  MICCO 145A  MAC145A     5660000SO                                                               TAILWHEEL ASSY  FRACTURED       P      O   OTHER                                                                                           O  OTHER                                                                         LDLANDING        1                      SW05121MA700  10                307                                     TAILWHEEL SPRING FAILED ON LANDING.  BROKEN IN MULTIPLE LOCATIONS. ONE BREAK POINT SHOWS EVIDENCE OF CORROSION, THE OTHER DOES NOT.  CRYSTALLIZATION PRESENT AT BOTH BREAK POINTS.  CRACKS APPEAR TO HAVE BEEN COVERED BY PAINT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L71 3O    RC                             
20060815000112006081500011SO  2006       8          15         2006FA0000774    120060806G3220                SPRING                                  MICCO 145A  MAC145A     5660000SO                                                               TAILWHEEL ASSY  FRACTURED       P      O   OTHER                                                                                           O  OTHER                                                                         LDLANDING        1                      SW05121MA700  10                307                                     TAILWHEEL SPRING FAILED ON LANDING.  BROKEN IN MULTIPLE LOCATIONS.  ONE BREAK POINT SHOWS EVIDENCE OF CORROSION, THE OTHER DOES NOT.  CRYSTALLIZATION PRESENT AT BOTH BREAK POINTS.  CRACKS APPEAR TO HAVE BEEN COVERED BY PAINT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L71 3O    RC                             
20060815000062006081500006SO  2006       8          15         2006FA0000775    120060810G57116707003         SPAR                                    PIPER PA28  PA28R180    7102809SO                                                               RT WING         CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO153894T5260                   28R30223                                DURING COMPLIANCE, A CRACK WAS FOUND ON THE MAIN SPAR DIRECTLY BEHIND THE SWIVEL BOLT BRACKET AT THE IB MOUNTING NUTPLATE. THE CRACK IS 3 INCHES IN LENGTH AND CURVES UPWARD ON BOTH ENDS. THE CRACK WAS NOT VISIBLE UNTIL THE AREA WAS CLEANED. IT IS RECOMMENDED THAT THIS AREA OF THE SPAR BE CLEANED AND INSPECTED DURING COMPLIANCE OF SB.  A CRACK WAS ALSO FOUND ON ANOTHER PA28R-180 NEAR THE SAME LOCATION ON THE SPAR. THIS INFORMATION AND PICTURES WERE SENT TO FOR EVALUATION.                                                                                                                                                                                                                                                     1L71 3O      2A13                         
20060815000012006081500001    2006       8          15         2006FA0000776    420060804G2300                ELEC CONNECTOR                          DIAMONDA40  DA40        2990002GL                                                               MICROPHONE      SHORTED         B      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      CE0538CF                        40567                                   ADJACENT MIC AND PHONE JACKS SHORTED TOGETHER CAUSING SQUEAL IN AUDIO SYSTEM.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1L71 3O    NTA47CE                        
20060815000092006081500009SO  2006       8          15         2006FA0000778    120060801G2842                TRANSMITTER                             PIPER PA46  PA46350P    7104602SO  LYC   O540  TIO540AE2A  41532EA                              FUEL SYSTEM     UNRELIABLE      C      O   OTHER                                                                                           N  FALSE WARNING                                                                 NRNOT REPORTED   1                      SW17319RD                       4636139                                 NEW-STYLE FUEL SENDERS UNRELIABLE.  HAVE REPLACED 3 TIMES SO FAR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L71 3O3  ORTA25SO   E14EA                
20060815000102006081500010SO  2006       8          15         2006FA0000779    120060801G2842                TRANSMISSION                            PIPER PA46  PA46350P    7104602SO  LYC   O540  TIO540AE2A  41532EA                              ZONE 500        UNRELIABLE      C      O   OTHER                                                                                           N  FALSE WARNING                                                                 NRNOT REPORTED   1                      SW17319RD                       4636139                                 NEW-STYLE FUEL SENDERS UNRELIABLE.  HAVE REPLACED 3 TIMES SO FAR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L71 3O3  ORTA25SO   E14EA                
20060815000042006081500004CE  2006       8          15         2006FA0000780    120060808G3230NAS464P426      BOLT            CESSNA                  CESSNA340   340A        2076405CE                                                               BELL CRANK      SHEARED         C      A   UNSCHED LANDING                                                                                 S  AFFECT SYSTEMS                                                                LDLANDING        1                      SW172745F2113                   340A0949                                FAILURE OF THE PIVOT BOLT ON THE RT MLG DOWNLOCK BELLCRANK (BOOMERANG) APPEARS TO HAVE RESULTED FROM SHEAR FORCES DURING LANDING. FORCES OF THIS NATURE EXCEEDED DESIGN LIMITS OF THIS SEGMENT OF THE LANDING GEAR SYSTEM.  THE EXACT CAUSE COULD NOT BE DETERMINED BUT MAY HAVE RESULTED FROM IMPROPER RIGGING TO THE SYSTEM DURING RECENT MAINTENANCE OF THE LANDING GEAR COMPONENTS.                                                                                                                                                                                                                                                                                                                                                         1L72 3O      3A25                         
20060815000052006081500005CE  2006       8          15         2006FA0000781    120060803G5544905000377       BRACKET                                 BEECH 90    C90         1152913CE                                                               RUDDER          UNSECURE        B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL1136799200                    LJ1799                                  DURING THE INITIAL 200 HOUR PHASE 1 INSPECTION ON THIS AIRCRAFT, THE MOUNT BRACKETS THAT SECURE THE RUDDER SERVO BRIDLE CABLES AND PULLEYS WERE FOUND TO BE UNSECURED AT THE AFT ATTACH POINTS (FS 364.00) BOTH LT AND RDT BRACKETS WERE NOT ATTACHED. THE ASSOCIATED FUSELAGE (2 EACH BOLTS IAW SIDE WAS LOCATED IN THE AFT FUSELAGE COMPARTMENT. REVIEWED OF THE AIRFRAME LOGBOOKS DETERMINE NO DOCUMENTED WORK HAD BEEN PERFORMED IN THE AREA OR ON THE AFFECTED COMPONENTS. RAYTHEON FIELD TECHNICAL SUPPORT IS CONDUCTING AN INVESTIGATION.                                                                                                                                                                                                1L72 3T      3A20                         
20060821000662006082100066EA  2006       8          21         2006FA0000782    120060802G2810G201G202        FITTING                                 FOUND FBA   FBA2C       3640102EA  LYC   O540  IO540*      41532EA                              FUEL SYSTEM     UNDERTORQUED    H      K   NONE                                                                                            WK INADEQUATE Q C            FLUID LOSS                                          ININSP/MAINT     1                      AL03753  532                    44                                      AS REPORTED FROM THE PILOT, THE MAINTENANCE VENDOR FOUND NUMEROUS FUEL FITTINGS WHICH CONNECT THE FUEL LINES TO THE HEADER TANKS TO BE SEEPING FUEL. APPROXIMATE TIME OF SERVICE 532 HOURS. PIPE THREADED FITTINGS HAD NO THREAD LUBE/SEALANT. THE VENDOR NOTED THAT THE FUEL FITTINGS WERE NOT PROPERLY TORQUED.  THIS MAY REPRESENT A QUALITY CONTROL ISSUE AT THE FOUND AIRCRAFT PRODUCTION FACILITY. AT PRESENT THE USDOI, AVIATION MANAGEMENT DIRECTORATE, IS INVESTIGATING THIS EVENT WITHIN ITS FLEET.                                                                                                                                                                                                                                   1H71 3O3  O  A7EA    1E4                  
20060816002652006081600265CE  2006       8          16         2006FA0000783    120060725G251007140593        SEAT                                    CESSNA182   182R        2072731CE                                                               COCKPIT         BROKEN          B  BIIRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA219983H4070                   18268161                                INSPECTED SEATS IAW AD.  FOUND PILOTS SEAT BOTTOM ASSY BROKEN AT LT FWD ATTACH POINT AND RT FWD CRACKED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1L71 3O    NT3A13                         
20060816003022006081600302    2006       8          16         2006FA0000784    420060814G2562300011          ELT                                     CESSNA172   172S        2072439CE                                                               CABIN           FAILED          B      K   NONE                                                                                            L  NO TEST                                                                       ININSP/MAINT     1                      SW055359K1944 1944              9447                                    ELT REMOTE SWITCH FOUND TO BE INOP. ELT SENT TO SHOP FOR REPAIR, SYSTEM OPS CKD NORMAL AFTER REPAIR. THIS IS THE 4 OCCURRENCE OF THIS ON THIS TYPE AIRCRAFT IN THE LAST 3 MONTHS. ALL REPAIRS ARE THE SAME REPLACE FUSE F1.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1H71 3O    NT3A12                         
20060816002262006081600226CE  2006       8          16         2006FA0000785    120060804G8011                MOTOR                                   CESSNA172   172P        2072436CE  LYC   O320  O320*       41508EA                              STARTER         SHORTED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA0399465                       17276450                                LIGHT WEIGHT STARTER MOTOR FAILED (SHORTED INTERNALLY) AFTER 1.5 YEARS SERVICE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H71 3O3  ONT3A12    E274                 
20060817001702006081700170CE  2006       8          17         2006FA0000786    120060804G801185034007        DRIVE GEAR                              CESSNA172   172R        2072401CE  LYC   O360  IO360B1E    41514EA                              STARTER         BROKEN          B      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA03981CP                       17280215                                BENDIX DRIVE GEAR BROKE INTO PIECES AFTER 1 YEAR OF SERVICE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1H71 3O3  ONT3A12    1E10                 
20060816003002006081600300SW  2006       8          16         2006FA0000787    120060811G53112722019045      FRAME                                   SWRNGNSA227 SA227AC     8780603SW                                                               FUSLEAGE        CRACKED         B  OWFRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE05ECIXL                       AC689                                   DURING REPAIR OF WING SPAR SHEAR WEB IAW AD AND SRM, IT WAS FOUND THAT THE LT AND RT BELT FRAMES WERE CRACKED AT THE STRINGER 11 CUTOUT.  THE CRACKED BELT FRAMES WILL BE REPLACED WITH NEW COMPLETION OF THE SPAR REPAIR.  AIRCRAFT IS OPERATING ON THE SPANISH REGISTER.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4T    RTA8SW                         
20060818001602006081800160SW  2006       8          18         2006FA0000788    120060811G57112722019046      FRAME                                   SWRNGNSA227 SA227AC     8780603SW                                                               WING            CRACKED         B  OWFRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE05ECIXL22492                  AC689                                   DURING REPAIR OF WING SPAR SHEAR WEB IAW AD AND SRM, IT WAS FOUND THAT THE LT AND RT BELT FRAMES WERE CRACKED AT THE STRINGER 11 CUTOUT.  THE CRAKED BELT FRAMES WILL BE REPLACED WITH NEW UPON COMPLETION OF THE SPAR REPAIR.  AIRCRAFT IS OPERATING ONT HE SPANISH REGISTER AS ECIXL.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4T    RTA8SW                         
20060817001732006081700173SO  2006       8          17         2006FA0000789    220060809G8530                CYLINDER                                BEECH 58    58          1152740CE  CONT  O520  IO520*      17032SO                              ENGINE          DAMAGED         B  CTURK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL2158LF                        TH237       243832R                     ON ANNUAL INSPECTION, WORK WAS BEING PERFORMED TO REPAIR OIL LEAK ON PUSH ROD TUBE SEALS, WHEN PUSHRODS WERE REMOVED, THEY WERE FOUND TO BE BENT AND GREATER THAN 50 PERCENT OF TOTAL TUBE WORN THROUGH.  FURTHER INVESTIGATION FOUND THAT SEVERAL TUBES WERE FOUND IN SAME CODITION AND THAT ALL EXHAUST RODS WERE BENT.  THERE WERE ALSO SIGNS ON 5 PISTONS OF VALVE CONTACT.  FIREWALL FWD RECONDITIONED CYLINDERS AND STATED THAT VALVE GUIDES HAD COAKING ON THEM AND THAT THE PISTON RINGS HAD LOST THEIR TEMPER.  OWNER IS SUSPECT OF BAD PARTS FROM MFG.  (K)                                                                                                                                                                           1L72 3O3  O  3A16    E5CE                 
20060817001692006081700169SW  2006       8          17         2006FA0000790    120060801G57115262L           SPAR                                    BBAVIA7     7HC         21101PNSW  LYC   O290  O290        41506EA                              WING            CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NE058906R                       7HC26                                   LONGITUDINAL CRACK FROM STRUT BOLT HOLE OB.  PROBABLE CAUSE: WING DAMAGE FROM PAST GROUND LOOPING PROPAGATING OVERTIME.  TIME OF INCIDENT IN LOGS, 7/17/72.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1H71 3O3  O  A759    E229                 
20060821000652006082100065CE  2006       8          21         2006FA0000791    120060708G272035660033        HINGE                                   BEECH P35   P35         1151530CE  CONT  O470  IO470*      17026SO                              RUDDERVATOR     CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP079520Y                       D7016                                   FAIRLEADS IN RUDDERVATOR TRIM TAB CNTRL CABLE SYS ARE CRACKING UPON INSTALLATION, POSSIBLY DURING FLIGHT.  BUTTON-HEAD RIVETS ARE INTERFERING WITH INSTALLATION, CAUSING CRACKS TO FORM IN (TANG) OF FAIRLEADS.  CABLE TENSION USED IN RUDDERVATOR TRIM TAB CABLES IS A FACTOR IN CRACKING.  A LOOSENING OF RUDDERVATOR TRIM TAB CNTRL CABLES IS NECESSARY DURING INSTALL, FOLLOWED BY RIGGING TO VERIFY PROPER CABLE TENSION.  A SMALL AMOUNT OF FILING ON BACK OF (TANG) OF FAIRLEAD FOR CLOSE TOLERANCE OF RIVETS THAT HOLD NUTPLATE FOR MOUNTING OF FAIRLEAD.  EITHER A NEW MATERIAL NEEDS TO BE EXPLORED FOR MAKING  FAIRLEADS MORE DURABLE, OR A MAINT NOTE NEEDS TO BE MADE ON PROPER INSTALLATION OF FAIRLEADS TO PREVENT CRACKING.  (K)1L71 3O3  ORT3A15    E1CE                 
20060816003412006081600341CE  2006       8          16         2006FA0000792    120060728G325024670036        BUNGEE CYLINDER                         CESSNA172   172RG       2072438CE  LYC   O360  O360*       41514EA                              NLG STEERING    BROKEN          D  V36RK   NONE                                                                                            O  OTHER                                                                         TXTAXI/GRND HDL  1                      SO1320CU                        172RG0323                               THE NOSE GEAR STEERING BUNGEE PN 2467003-6, BROKE WHILE TAXIING IN AFTER LANDING.  THE AIRCRAFT STOPPED WITHOUT INCIDENT.  THE BREAK OCCURRED IN THE  THEADED AREA OF THE SHAFT THAT CONTAINS THE CHAIN SPROCKET.  NOTE THAT THIS SHAFT HAS THREADS ON BOTH ENDS.  THE END THAT BROKE HAS THE SMALLER THREADS (.3125 INCHES) NAD IS ON THE OPPOSITE END FROM THE SPROCKET.  THIS FAILURE IS SIGNIFICANT BECAUSE WHEN THE BUNGEE BREAKS THE BODY, WILL PIVOT DOWN AROUND THE ATTACHMENT POINT AND FOUL THE ELEVATOR CONTROLS.  BUNGEE WAS REPLACED AT TACH 532 AS A RESULT OF THE AD.  THE AC HAS 8070 HRS ON IT SO THE REPLACEMENT PART  HAS 7538 HOURS ON IT.  (K)                                                                             1H71 3O3  O  3A17    E286                 
20060818001542006081800154CE  2006       8          18         2006FA0000793    120060628G5711                SPAR                                    BEECH 18    E18S        1151006CE  PWA   R985  R985*       52008NE                              LT WING         CORRODED        B  O31RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW1192WA 6600                   BA379                                   THE DEFECT IS SEVERE CORROSION IN SPAR TUBE LT SIDE UPPER AT WING STA 90.  PROBABLE CAUSE IS EXPOSURE TO MOISTURE OVER AN EXTENDED PERIORD OF TIMEM.  RECOMMENDATION TO PREVENT RECURRENCE WOULD BE TO SEAL AND FILL WITH LIN SEED OIL.  FURTHER RECOMMENDATION WOULD BE TO ADD A SPLICE TO SPARE SECTION TO PROVIDE STRUCTURE INTEGRITY.  FURTHER RECOMMENDATION WOULD BE TO VISUAL INSPECT AND DYE PENETRANT INSPECT THIS AREA AT 25 HOUR INTERVALS UP TO 1ST 100 HOURS.  IF NO FATIGUE OR CRACKS ARE NOTED THEN EXTEND VISUAL AND PENETRANT INSP TO EVERY 100 HOURS OR EACH YEAR WHICH EVER OCCURS FIRST.  SEE ATTACHED XRAY, PENETRANT REPORT AND ADDITIONAL AREAS OF CONCERN FOR NOTED DEFECT.  (K)                                        1L72 3R3  R  A765    5E1                  
20060818001492006081800149EA  2006       8          18         2006FA0000794    120060708G3210A153034         LEG ASSY                                GRUMANSA16  G64                EA  PWA   PT6   PT6A20      52043EA  HARTZLHCB3T HCB3TN3     GL  RT MLG          FAILED          D  NHXGK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP259965                        1362        21758       BUA20843        THE RT MAIN GEAR LEG (SPRING GEAR STYLE) FAILED AT THE UPPER END, JUST OB OF THE CLAMP BAV.  THIS IS AN AREA OF MAJOR FLEX OF THE GEAR LEG AND IT IS THE THICKEST PART OF THE LEG.  IN 25 YEARS WORKING ON THIS TYPE OF AIRCRAFT, I HAVE NEVER SEEN A FAILURE OF THE MAIN GEAR LEGS.  THIS SET OF GEAR WAS INSTALLED ON THE AIRCRAFT 4/22/02 AND WAS MAGNAFLUXED, SANDBLASTED, AND PAINTED PRIOR TO INSTALLATION.  THE GEAR LEGS WERE A USED SET AT THAT TIME AND THE TT ON THE PAIR IS UNKNOWN.  THE TIME SINCE MAGNAFLUX AND INSTALLATION (4/22/02) IS 1687.1 HRS.  THIS IS NOT A COMMON FAILURE AND I DO NOT BELIEVE THAT THERE IS A NEED FOR AN AD NOTE OR OTHER ACTION.  (K)                                                               2H72 4R3  T  EXPA2H72E4EA    6  CP15EA    
20060817001892006081700189NE  2006       8          17         2006FA0000795    120060524G64106516100001043   SPAR                                    SKRSKYS64   S64E        8142604NE  PWA   JFTD12JFTD12A4A   52047NE                              T/R BLADE       CRACKED         B  JYDRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM09229AC39689                  64018                                   (REF NR: MDR06-088)  IB SIDE OF SPAR ON TRAILING EDGE HAS A CRACK.  THE CRACK IS APPROX .482 INCH LONG AND RUNS FROM TIP END OF BLADE, DOWN INTO THE SCREW HOLE COUNTERSINK.  BLADE HAS ACCUMULATED 660.4 HOURS SINCE LAST REPAIR.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2G72 4U4  U  H4EA    E15EA                
20060817001712006081700171CE  2006       8          17         2006FA0000796    120060721G2910S217840105      HYDRAULIC LINE                          CESSNA172   172RG       2072438CE                                                               HYDRAULIC SYS   FAILED          D      O   OTHER                                                                                           K  FLUID LOSS                                                                    CRCRUISE         1                      CE035114U                       172RG0243                               NOSE GEAR HYDRAULIC ACTUATOR HOSE BLEW OUT OF CRIMP IN FLIGHT CAUSING LOSS OF ALL HYDRAULIC FLUID AND GEAR WOULD NOT GO UP OR DOWN, EVEN WITH HAND PUMP.  THE MFG HOSE WAS NOT THE AEROQUIP TYPE WITH STEEL BRADING OR THE SCREW ON ENDS.  RECOMMEND THE AEROQUIP 303 HIGH PRESSURE HOSE COULD NOT FIND A TT ON HOSE OR A DATE CODE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3O      3A17                         
20060817001832006081700183    2006       8          17         2006FA0000798    420060802G6122210638F         GOVERNOR                                                                                                                                PROPELLER       FAILED          B  IG0RO   OTHER                                                                                           O  OTHER                                                                         ININSP/MAINT     1                      NM03                                                                    THE GOVERNOR FAILED AFTER 106 HOURS OF OPERATION.  THIS UNIT WILL NOT PERFORM THE OVERSPEED TEST.  COMPONENT WAS OVERHAULED ON WO 39044 ON 5/18/06. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   
20060817001752006081700175    2006       8          17         2006FA0000799    420060804G61228210024H        GOVERNOR                                                                                                                                PROPELLER       FAILED          B  IG0RO   OTHER                                                                                           O  OTHER                                                                         ININSP/MAINT     1                      NM03                                                                    THE GOVERNOR FAILED AFTER 772.1 HOURS OF OPERATION.  PROPELLER SYNCHRONIZATION FUNCTION IS INOPERATIVE.  COMPONENT WAS OVERHAULED ON WO 39914 ON 07/06/2006.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         
20060817001802006081700180    2006       8          17         2006FA0000800    420060527G6122210638          GOVERNOR                                                                                                                                PROPELLER       UNKNOWN         B  IG0RO   OTHER                                                                                           O  OTHER                                                                         ININSP/MAINT     1                      NM03                                                                    DOCUMENTATION RECEIVED WITH COMPONENT AFTER REPAIR DOES NOT SHOW TIME SINCE OVERHAUL. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 
20060817001852006081700185    2006       8          17         2006FA0000801    420060413G61228210406H        GOVERNOR                                                                                                                                PROPELLER       FAILED          B  IG0RO   OTHER                                                                                           O  OTHER                                                                         ININSP/MAINT     1                      NM03                                                                    BETA VALVE STICKING CAUSING AIRCRAFT TO YAW DURING ENGINE POWER REDUCTION.  GOVERNOR FAILED 291 HOURS AFTER INSTALLATION. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             
20060817001842006081700184    2006       8          17         2006FA0000802    420060207G6122210638F         FASTENER                                                                                                                                PROP GOVERNOR   LOOSE           B  IG0RO   OTHER                                                                                           O  OTHER                                                                         ININSP/MAINT     1                      NM03                                                                    COMPONENT RECEIVED FROM OVERHAUL SHOP WITH HARDWARE LOOSE ON CONNECTOR.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              
20060817001862006081700186    2006       8          17         2006FA0000803    420060221G61228210406         GOVERNOR                                                                                                                                PROPELLER       FAILED          B  IG0RO   OTHER                                                                                           O  OTHER                                                                         ININSP/MAINT     1                      NM03                                                                    GOVERNOR WOULD NOT PASS TEST AFTER INSTALLATION.  PROPELLER RPM DOES NOT DECREASE TO 1150 RPM WHEN TEST SWITCH ACTIVATED.  UNIT WILL ALSO NOT PASS PY SHIFT TEST.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    
20060817001882006081700188    2006       8          17         2006FA0000804    420060620G61228210406H        GOVERNOR                                                                                                                                PROPELLER       FAILED          B  IG0RO   OTHER                                                                                           O  OTHER                                                                         ININSP/MAINT     1                      NM03                                                                    BETA VALVE STICKING, CAUSING AIRCRAFT TO YAW DURING ENGINE POWER REDUCTION.  GOVERNOR FAILED 171 HOURS AFTER INSTALLATION.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           
20060817001772006081700177    2006       8          17         2006FA0000805    420060629G61228210406H        GOVERNOR                                                                                                                                PROPELLER       FAILED          B  IG0RO   OTHER                                                                                           O  OTHER                                                                         ININSP/MAINT     1                      NM03                                                                    BETA VALVE STICKING CAUSING AIRCRAFT TO YAW DURING ENGINE POWER REDUCTION.  GOVERNOR FAILED 302.6 HOURS AFTER INSTALLATION.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          
20060817001812006081700181    2006       8          17         2006FA0000806    420060502G6122210638F         GOVERNOR                                                                                                                                PROPELLER       FAILED          B  IG0RO   OTHER                                                                                           O  OTHER                                                                         ININSP/MAINT     1                      NM03                                                                    GOVERNOR WOULD NOT ACTIVATE USING TEST SWITCH ON INSTALLATION AFTER OVERHAUL. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         
20060817001782006081700178    2006       8          17         2006FA0000807    420060207G61228210406         GOVERNOR                                                                                                                                PROPELLER       FAILED          B  IG0RO   OTHER                                                                                           O  OTHER                                                                         ININSP/MAINT     1                      NM03                                                                    GOVERNOR WOULD NOT PASS TEST AFTER INSTALLATION.  PROPELLER RPM DOES NOT DECREASE TO 1150 RPM WHEN TEST SWITCH ACTIVATED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            
20060817001742006081700174    2006       8          17         2006FA0000808    420060207G612282100224H       GOVERNOR                                                                                                                                PROPELLER       FAILED          B  IG0RO   OTHER                                                                                           O  OTHER                                                                         ININSP/MAINT     1                      NM03                                                                    BETA VALVE STICKING WHEN ENGINE POWER IS REDUCED CAUSING AIRCRAFT TO YAW.  GOVERNOR FAILED 222 HOURS OF OPERATION AFTER OVERHAUL.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    
20060817001792006081700179    2006       8          17         2006FA0000809    420060519G612282130391        GOVERNOR                                                                                                                                PROPELLER       MISMANUFACTURED B  IG0RO   OTHER                                                                                           O  OTHER                                                                         ININSP/MAINT     1                      NM03                                                                    COMPONENT RECEIVED WITH INCORRECT ARM INSTALLED ON BETA VALVE.  ATTACHMENT HOLE FOR LINKAGE WAS TOO SMALL.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           
20060817001762006081700176    2006       8          17         2006FA0000810    420060620G612258210007        GOVERNOR                                                                                                                                PROPELLER       FAILED          B  IG0RO   OTHER                                                                                           O  OTHER                                                                         ININSP/MAINT     1                      NM03                                                                    PROPELLER GOVERNOR FAILED AFTER 2.5 HOURS OF OPERATION AFTER OVERHAUL. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                
20060817001822006081700182    2006       8          17         2006FA0000811    420060616G6122210638F         GOVERNOR                                                                                                                                PROPELLER       OUT OF ADJUST   B  IG0RO   OTHER                                                                                           O  OTHER                                                                         ININSP/MAINT     1                      NM03                                                                    DURING TEST AFTER INSTALLATION, PROPELLER DROPS TO 1800 RPM.  GOVERNOR SET TO INCORRECT LIMIT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       
20060817001872006081700187    2006       8          17         2006FA0000812    420060613G61228210406H        GOVERNOR                                                                                                                                PROPELLER       FAILED          B  IG0RO   OTHER                                                                                           O  OTHER                                                                         ININSP/MAINT     1                      NM03                                                                    BETA VALVE STICKING CAUSING AIRCRAFT TO YAW DURING ENGINE POWER REDUCTION.  GOVERNOR FAILED 36 HOURS AFTER INSTALLATION. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              
20060825000242006082500024CE  2006       8          25         2006FA0000816    120060815G2810                O-RING                                  CESSNA182   182D        2072710CE                                                               FUEL CAP        SPLIT           D      O   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      SW058916X300                    18253316                                THE RT FUEL TANK CAP O-RING SPLIT AND FUEL SIPHONED OUT OF THE RT TANK DURING FLIGHT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1H71 3O    NT3A13                         
20060821000572006082100057SO  2006       8          21         2006FA0000817    220060816G74146310            MAGNETO                                 BEECH 55    E55         1152732CE  CONT  O520  IO520C      17032SO                              LT ENGINE       SEPARATED       B      O   OTHER                                                                                           RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      SO131850F1600                   TE1195                                  LT ENGINE OB MAGNETO IMPULSE COUPLING FROZE UP, CAUSING MAGNETO HOUSING TO COMPLETELY SEPARATE FROM ENGINE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L72 3O3  O  3A16    E5CE                 
20060825000332006082500033SO  2006       8          25         2006FA0000819    220060709G8530656612          EXHAUST VALVE                           BBAVIA7     7EC         2110120SW  CONT  C90   C9012F      17009SO                              NR 4 CYLINDER   BROKEN          B  AWORO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL154715E1350                   7EC59       42615012                    WHEN THE NR 4 CYLINDER WAS REMOVED, THE EXHAUST VALVE HEAD WAS FOUND TO BE BROKEN OFF, ABOUT .5 INCH FROM THE FACE OF THE VALVE, CAUSING FAILURE OF THE PISTON AND FAILURE OF THE INTAKE VALVE.  THE CIRCUMSTANCES OF THE FAILURE CAUSED A LOSS OF ENGINE POWER AND A FORCED LANDING IN A FIELD.  THE PILOT WAS UNHARMED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                  1H71 3O3  O  A759    E252                 
20060825000472006082500047CE  2006       8          25         2006FA0000820    120060706G2910511700712       TUBE                                    CESSNA425   425         2076018CE                                                               HYD SYSTEM      FAILED          D      O   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      WP05                                                                    TUBE FAILED ON LOWER ATTACHMENT, ALL FLUID LOST, CAUSE UNKNOWN.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L72 3T    RTA7CE                         
20060825000212006082500021CE  2006       8          25         2006FA0000821    120060726G5200                HINGE                                   CESSNA421   421C        2076016CE  CONT  O520  GTSIO520*   17032SO                              DOOR            CORRODED        B  AW4RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP11485DS4783                   421C0459                                TO FIND USED SERVICEABLE HINGES AND HINGE SUPPORT FITTINGS FROM AC SALVAGE COMPANIES, EVERY HINGE THAT WAS RECEIVED, SAME TYPE OF CORROSION,  BEARING AND BUSHINGS WERE RUSTED TO HINGE BOLT.  BUSHINGS AND BEARING ARE PRESS FIT INTO HINGE SO AS TO ALLOW HINGE ASSY TO ROTATE ON BOLT.  WHEN BOLT FREEZES TO BEARING AND BUSHINGS,  BOLT THEN ROTATES IN SOFT ALUMINUM SUPPORT FITTING WHICH ALLOWS HOLES IN FITTING TO ELONGATE.  IT WOULD APPEAR THAT THIS IS A CHRONIC PROBLEM.  AS NOTED IN ORIGINAL MD PROBLEM SEEMS TO BE RELATED TO FACT THAT SUPPORT FITTINGS CAN RETAIN WATER.  THERE IS NO SPECIFIC INSPECTION REQUIREMENT TO CHECK THESE HINGES FOR CORROSION AND SO CONDITION REMAINS UNDETECTED UNTIL BOLTS HAVE TO BE REMOVED. 1L72 3O3  O  A7CE    E7CE                 
20060825000422006082500042SO  2006       8          25         2006FA0000822    120060303G32209617800         SPRING                                  PIPER PA34  PA34200     7103405SO  LYC   O360  IO360A1A    41514EA                              NLG             UNKNOWN         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL11210SK                       347250307                               WHEN COMPARING THE NEW SPRING TO OLD SPRING, USING A FISH SCALE, THE NEW TOOK 12 LBS TO OFFSET THE COILS THE OLD ONLY TOOK 7LBS.  THIS IS BELIEVED TO CONTRIBUTE TO NOSE GEAR COLLAPSE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L72 3O3  O  A7SO    1E10                 
20060825000432006082500043SO  2006       8          25         2006FA0000823    120060303G3220400890AN2340A   BOLT                                    PIPER PA34  PA34200     7103405SO  LYC   O360  IO360A1A    41514EA                              NLG DOWNLOCK    BENT            D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL11210SK                       347250307                               THIS WITH OTHER PROBLEMS LEAD TO SLOP IN THE DOWNLOCK OF THE NOSE GEAR.  THIS CONTRIBUTED TO THE COLLAPSE OF THE NOSE GEAR.  BOLT REPLACED WITH NEW.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 3O3  O  A7SO    1E10                 
20060825000222006082500022SO  2006       8          25         2006FA0000824    120060303G32309506189         BUSHING                                 PIPER PA34  PA34200     7103405SO                                                               NLG DOWLOCK     BROKEN          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL11210SK                       347250307                               INSPECTION REVEALED END OF BUSHING HAD BROKE OFF.  REPLACE WITH NEW.  THIS CONTRIBUTED TO SLOP IN NOSE GEAR DOWNLOCK MECHANISM AND GEAR COLLAPSE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L72 3O      A7SO                         
20060831000292006083100029CE  2006       8          31         2006FA0000825    120060804G2730MS21251B6L      TURNBUCKLE                              BEECH B300  B300        1159232CE                                                               ELEVATOR        MISMANUFACTURED B  E81RK   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      GL038YN  697                    FL417                                   WHEN THE PART WAS MFG, THE SAFETY SLOT DID NOT LIME UP WITH THE END SLOTS.  THIS DID NOT CAUSE A PROBLEM EITHER OPERATIONALLY, OR IN THE PROCESS OF SAFETYING THE TURNBUCKLE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4T    RTA24CE                        
20060831000072006083100007CE  2006       8          31         2006FA0000826    120060727G271005010105364     CONTROL CABLE                           CESSNA172   172S        2072439CE  LYC   O360  IO360A1A    41514EA                              LT AILERON      FRAYED          B  7TFRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP07533BM                       172S8340                                DURING AN ANNUAL INSPECTION OF THE AIRFRAME IT WAS FOUND THAT THE LT AILERON  CROSSOVER CABLE WAS FRAYED AT THE ABBRASSION STRIP.  THE PROBABLE CAUSE IS THE CABLE RUBBING AGAINST THE ABBRASION BLOCK.  A POSSIBLE SOLUTION IS TO MAKE THE ABBRASION BLOCK OUT OF A SOFTER MATERIAL.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                      1H71 3O3  ONT3A12    1E10                 
20060825000542006082500054CE  2006       8          25         2006FA0000827    120060727G271005010105362     CONTROL CABLE                           CESSNA172   172S        2072439CE  LYC   O360  IO360A1A    41514EA                              RT WING         UNSERVICEABLE   B  7TFRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP07533BM5687                   172S8340                                DURING AN ANNUAL INSPECTION OF THE AIRFRAME IT WAS FUND THAT THE RT AILERON DIRECT CABLE WAS FRAYED AT THE FAIRLEAD ASSEMBLY.  THE PROBABLE CAUSE IS THE CABLE RUBBING AGAINST THE FAIRLEAD ASSY.  A POSSIBLE SOLUTION IS TO MAKE THE FAIRLEAD ASSY OUT OF A SOFTER MATERIAL.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O3  ONT3A12    1E10                 
20060831000062006083100006CE  2006       8          31         2006FA0000828    120060727G271005010105365     CONTROL CABLE                           CESSNA172   172S        2072439CE                                                               RT AILERON      FRAYED          B  7TFRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP07533BM5687                   172S8340                                DURING AN ANNUAL INSPECTION OF THE AIRFRAME IT WAS FOUND THAT THE RT AILERON CROSSOVER CABLE WAS FRAYED AT THE FAIRLEAD ASSY.  THE PROBABLE CAUSE IS THE CABLE RUBBING AGAINST THE FAIRLEAD ASSY.  A POSSIBLE SOLUTION IS TO MAKE THE FAIRLEAD ASSY OUT OF A SOFTER MATERIAL.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O    NT3A12                         
20060825000452006082500045SO  2006       8          25         2006FA0000829    220060809G74146320            POINTS          SLICK                   AMTR  LANCARLC41550FG   5150001GL  CONT  O550  TSIO550C         SO                              MAGNETO         BROKEN          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NE02400UK           653280      41062       802709                      MAGNETO FAILURE, ON ECR ON INSP RT MAGNETO POINT HAD BROKEN IN HALF.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L71 3O3  ORTEXPA1L71E5SO                 
20060825000552006082500055CE  2006       8          25         2006FA0000830    120060807G3246MS20002C6       WASHER                                  RAYTHN390   390         7150030CE                                                               MLG WHEEL       MISINSTALLED    B  E81RO   OTHER                                                                                           W  INADEQUATE Q C                                                                NRNOT REPORTED   1                      GL03390JV           0453        RB129                                   DURING WHEEL DISASSEMBLY FOR TIRE REPLACEMENT FOUND WHEEL TIE BOLT CHAMFERED WASHERS INSTALLED INCORRECTLY, WITH CHAMFERED SIDES TOWARDS WHEEL HALF.  NOTED WASHERS TO BE BENT, WHEEL TIE BOLT HEADS UNDERSIDE RADIUSES DAMAGED.  SUSPECT TECHNICIAN ASSEMBLING WHEELS AT PREVIOUS TIRE CHANGE AT ANOTHER FACILITY DID NTO FULLY FOLLOW COMPONENT MM AND WAS NOT FAMILIAR WITH INSTALLATION OF MS20002 SERIES CHAMFERED WASHERS.  (K)                                                                                                                                                                                                                                                                                                           17 2 3F    RTA00010WI                     
20060831000282006083100028CE  2006       8          31         2006FA0000831    120060807G3246MS20002C6       WASHER                                  RAYTHN390   390         7150030CE                                                               WHEEL           MISINSTALLED    B  E81RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03390JV284                    RB129                                   DURING WHEEL DISASSEMBLY FOR TIRE REPLACEMENT FOUND WHEEL TIE BOLT CHAMFERED WASHERS INSTALLED INCORRECTLY, WITH CHAMFERED SIDES TOWARDS WHEEL HALF.  NOTED WASHERS TO BE BENT, WHEEL TIE BOLT HEADS UNDERSIDE RADIUSES DAMAGED.  SUSPECT TECHNICIAN ASSEMBLY WHEELS AT PREVIOUS TIRE CHANGE AT ANOTHER FACILITY DID NOT FULLY FOLLOW COMPONENT MM AND WAS NOT FAMILIAR WITH INSTALLATION OF MS20002 SERIES CHAMFERED WASHERS.  (K)                                                                                                                                                                                                                                                                                                             17 2 3F    RTA00010WI                     
20060825000252006082500025CE  2006       8          25         2006FA0000832    120060726G32341SX1T           SWITCH                                  BEECH MU300 400A        1155402CE                                                               MLG SELECTOR    DAMAGED         B  E81RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL03334SR3446                   RK129                                   DURING SCHEDULED INSPECTION, FOUND LANDING GEAR WARNING HORN WOULD NOT OPERATE WITH LT POWER LEVER RETARDED.  FOUND THROTTLE QUADRANT SWITCHES S25 AND S26 TO HAVE HIGH INTERNAL RESISTANCE.  REPLACED SWITCHES AND ADJUSTED AS REQUIRED IAW MM.  LANDING GEAR WARNING SYSTEM TESTS NORMAL.  TYPICAL FAILURE MODE FOR THIS TYPE SWITCH USED ON THROTTLE LEVERS FOR VARIOUS FUNCTIONS.  RECOMMEND A MORE EXTENDED LIFE SWITCH BEING UTILIZED, OR ESTABLISH A SCHEDULED 2600 HR REPLACEMENT SCHEDULE (IN CONJUNCTION WITH REPLACEMENT SCHEDULE (IN CONJUNCTION WITH ADDITIONAL C-INSPECTION/COMPONENT REPLACEMENT ITEMS).  (K)                                                                                                                    2H72 4F    RTA16SW                        
20060825000402006082500040CE  2006       8          25         2006FA0000833    120060718G32405010614         BRAKE                                   BEECH MU300 400A        1155402CE                                                               MLG             SEIZED          B  E81RC   ABORTED TAKEOFF                                                                                 J  WARNING INDICATION                                                            TOTAKEOFF        1                      GL03476LX                       RK376                                   DURING INITIAL TAKEOFF ROLL, FOLLOWING POSITIVE PARKING BRAKE RELEASE CHECK, LT MAIN WHEEL BRAKE LOCKED-UP.  TAKEOFF ABORTED DUE TO SLOW ACCELERATION, POOR DIRECTIONAL CONTROL.  UNABLE TO MOVE AIRCRAFT UNTIL RT BRAKE APPLIED AND RELEASED, THEN TAXI-IN NORMAL.  REPLACED LT MAIN WHEEL BRAKE.  ALSO REPLACED PN 4500A2 PARKING BRAKE VALVE ASSY.  AS A PRECAUTION IAW OPERATOR REQUEST.  REPLACED LT MAIN WHEEL ASSY.  DUE TO FLAT-SPOTTED TIRE.  AT THIS TIME SUSPECTED FAULT IS IN LT BRAKE ASSY, BRAKE ASSY.  QUARANTINED BY OPERATOR FOR FURTHER EVALUATION.  (K)                                                                                                                                                                      2H72 4F    RTA16SW                        
20060825000502006082500050NE  2006       8          25         2006FA0000834    220060728G7322D8531           LINK                                    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              THROTTLE ARM    SEPARATED       D      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             NRNOT REPORTED   1                      NM07494SH486                    10878       3043948A                    ON 7/26/06 PILOT REPORTED THAT WHILE FLYING THROTTLE CONTROL BECOME INEFFECTIVE.  AIRCRAFT LANDED SAFELY AT AIRFIELD AND PUSHED TO HANGAR.  INSPECTED THROTTLE CONTROL ATTACHMENT AT ENGINE THROTTLE BODY AND FOUND UPPER ROD END OF LINK, PN D8531 SEPARATED.  PHOTOGRAPH TAKEN AND SENT OT MFG, IAW INSTRUCTION , LINK PN B5642 ORDERED AND RETURNED THE SEPARATED LINK PN D8531 TO MFG FOR FURTHER INVESTIGATION.  (K)                                                                                                                                                                                                                                                                                                                       1G71 3O3  O  H11NM   1E4                  
20060825000442006082500044EA  2006       8          25         2006FA0000835    120060811G2500SPH1606B3       INVERTER                                CNDAIRCL600 CL6002B16   1900305EA  GE    CF34  CF341A           NE                              STATIC FREQUENCYMISINSTALLED    D      O   OTHER                                                                                           W  INADEQUATE Q C                                                                NRNOT REPORTED   1                      NE05372G                        5351                                    THIS STATIC FREQUENCY INVERTER WAS INSTALLED IN THE STATED AIRCRAFT ON JUNE 2, 2006.  AT THE TIME OF INSTALLATION, THE PART HAD BEEN OVERHAULED BY CONSOLIDATED AC SUPPLY CO, INC.  UNDER WO NR 7314, DATED MAR 14,2006.  THE STATIC FREQUENCY INVERTER FAILED ON AUGUST 8, 2006.                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F4  FRTA21EA   E15NE                
20060825000492006082500049EA  2006       8          25         2006FA0000836    120060811G2130                UNKNOWN                                 CNDAIRCL604 CL604       1900301EA  GE    CF34  CF34*            NE                              CABIN PRESSURE  UNKNOWN         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NE03373G                        5556                                    REASON REMOVED, PRESSURIZATION CLIMBS AFTER T/O UP TO 2000 FPM.  THEN CATCHES AND WORKS DURING FLIGHT.  PRIOR TO INSTALLATION IN THE AIRCRAFT, THIS COMPONENT WAS INSPECTED, UNDER WO NR U22732, DATED MAR 30, 2006.  COMPONENT WAS INSTALLED ON 06/09/2006.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F4  FRTA21EA   E15NE                
20060825000562006082500056CE  2006       8          25         2006FA0000837    120060607G261222412886        FIRE LOOP                               BEECH 1900  1900C       1154161CE  PWA   PT6   PT6A65B     52043EA                              RT NACELLE      BROKEN          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM07172GA                       UB11        PS32232                     PILOT EXPERIENCED A FIRE WARNING ANNUNCIATION DURING TAKEOFF ROLL.  PILOT ABORTED TAKEOFF.  MAINTENANCE FOUND THAT ONE FIRELOOP HAD FAILED AND CAUSED THE FALSE FIRE INDICATION.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4T4  TRTA24CE   E4EA                 
20060825000532006082500053    2006       8          25         2006FA0000839    120060822G32133581525115      BRACE           RAYTHN                                                                                                                  MLG STRUT       MISDRILLED      C      O   OTHER                                                                                           W  INADEQUATE Q C                                                                NRNOT REPORTED   1                      CE09                072                                                 THIS IS A NEW PART PURCHASED THRU MFG (RAPID).  BRACE ASSEMBLY HAS 4 BOLT HOLES THAT ARE NOT DRILLED TO THE REQUIRED SIZE TO ACCOMMODATE THE BOLT THAT IS TO BE INSTALLED.  HOLE I.D. SIZE IS 0.185.  BOLT O.D. SIZE IS 0.310.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            
20060825000282006082500028CE  2006       8          25         2006FA0000840    120060822G52803511513022      ANGLE                                   BEECH 36    A36         1151604CE                                                               MLG DOOR        CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL19     360                    E3384                                   DURING A ROUTINE ANNUAL INSPECTION IT WAS FOUND THAT BOTH THE LT AND RT IB GEAR DOOR AFT HINGE ANGLES (P/N'S 35-115130-22, -24, 35-115070-16 AND -18 WERE CRACKED.  IT IS MY OPINION THAT THIS IS DUE TO THE FACT THAT MFG HAS CHANGED THE DESIGN OF THE INBOARD GEAR DOOR FROM A STAMPED ASSY TO A MILLED PART.  THIS CONDITION OBVIOUSLY IS PRESENT IN OTHER LIKE MODELS AND BEECH HAS ACKNOWLEDGED THE PROBLEM IN THEIR PARTS BOOK AS THEY GIVE INSTRUCTIONS FOR ORDERING DIFFERENT PART NUMBERS.  THE NEW PART NUMBER PARTS ARE MADE FROM .050" ALUMINUM WHILE THE ORIGINAL PARTS WERE MADE FROM .032 INCHES ALUMINUM.  THE CRACKS COULD EASILY GO UNDETECTED AND A SB IS NEEDED TO HELP OTHERS FIND AND ELIMINATE THESE CRACKS.            1L71 3O      3A15                         
20060825000292006082500029CE  2006       8          25         2006FA0000841    120060822G52803511513022      ANGLE                                   BEECH 36    A36         1151604CE                                                               MLG DOOR        CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL19     360                    E3384                                   DURING A ROUTINE ANNUAL INSPECTION IT WAS FOUND THAT BOTH LT AND RT IB GEAR DOOR AFT HINGE ANGLES (P/N'S 35-115130-22, -24, 35-115070-16 AND -18 WERE CRACKED.  IT IS MY OPINION THAT THIS IS DUE TO FACT THAT MFG HAS CHANGED DESIGN OF THE IB GEAR DOOR FROM A STAMPED ASSY TO A MILLED PART.  THIS CONDITION OBVIOUSLY IS PRESENT IN OTHER LIKE MODELS AND MFG HAS ACKNOWLEDGED THE PROBLEM IN THEIR PARTS BOOK AS THEY GIVE INSTRUCTIONS FOR ORDERING DIFFERENT PN.  THE NEW PN PARTS ARE MADE FROM .050 INCH ALUMINUM WHILE ORIGINAL PARTS WERE MADE FROM .032 INCH ALUMINUM.  THE CRACKS COULD EASILY GO UNDETECTED AND A SB IS NEEDED TO HELP OTHERS FIND AND ELIMINATE THESE CRACKS.                                                    1L71 3O      3A15                         
20060825000302006082500030CE  2006       8          25         2006FA0000842    120060822G52803511513022      ANGLE                                   BEECH 36    A36         1151604CE                                                               MLG DOOR        CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL19     360                    E3384                                   DURING A ROUTINE ANNUAL INSPECTION IT WAS FOUND THAT BOTH THE LT AND RT IB GEAR DOOR AFT HINGE ANGLES (P/N'S 35-115130-22, -24, 35-115070-16 AND -18 WERE CRACKED.  IT IS MY OPINION THAT THIS IS DUE TO THE FACT THAT MFG HAS CHANGED THE DESIGN OF THE IB GEAR DOOR FROM A STAMPED ASSY TO A MILLED PART.  THIS CONDITION OBVIOUSLY IS PRESENT IN OTHER LIKE MODELS AND MFG HAS ACKNOWLEDGED THE PROBLEM IN THEIR PARTS BOOK AS THEY GIVE INSTRUCTIONS FOR ORDERING DIFFERENT PART NUMBERS.  THE NEW PN PARTS ARE MADE FROM .050 INCH ALUMINUM WHILE THE ORIGINAL PARTS WERE MADE FROM .032 INCH ALUMINUM.  THE CRACKS COULD EASILY GO UNDETECTED AND A SB IS NEEDED TO HELP OTHERS FIND AND ELIMINATE THESE CRACKS.                          1L71 3O      3A15                         
20060825000312006082500031CE  2006       8          25         2006FA0000843    120060822G52803511513022      ANGLE                                   BEECH 36    A36         1151604CE                                                               MLG DOOR        CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL19     360                    E3384                                   DURING A ROUTINE ANNUAL INSPECTION IT WAS FOUND THAT BOTH THE LT AND RT IB GEAR DOOR AFT HINGE ANGLES (P/N'S 35-115130-22, -24, 35-115070-16 AND -18 WERE CRACKED.  IT IS MY OPINION THAT THIS IS DUE TO THE FACT THAT MFG HAS CHANGED THE DESIGN OF THE IB GEAR DOOR FROM A STAMPED ASSY TO A MILLED PART.  THIS CONDITION OBVIOUSLY IS PRESENT IN OTHER LIKE MODELS AND MFG HAS ACKNOWLEDGED THE PROBLEM IN THEIR PARTS BOOK AS THEY GIVE INSTRUCTIONS FOR ORDERING DIFFERENT PN.  THE NEW PN PARTS ARE MADE FROM .050 INCH ALUMINUM WHILE THE ORIGINAL PARTS WERE MADE FROM .032 INCH ALUMINUM.  THE CRACKS COULD EASILY GO UNDETECTED AND A SB IS NEEDED TO HELP OTHERS FIND AND ELIMINATE THESE CRACKS.                                    1L71 3O      3A15                         
20060825000372006082500037CE  2006       8          25         2006FA0000847    120060822G52803511513022      ANGLE                                   BEECH 36    A36         1151604CE                                                               MLG DOOR        CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL1945MS 360                    E3384                                   DURING A ROUTINE ANNUAL INSPECTION IT WAS FOUND THAT BOTH THE LT AND RT IB GEAR DOOR AFT HINGE ANGLES (P/N'S 35-115130-22, -24, 35-115070-16 AND -18 WERE CRACKED.  IT IS MY OPINION THAT THIS IS DUE TO THE FACT THAT MFG HAS CHANGED THE DESIGN OF THE IB GEAR DOOR FROM A STAMPED ASSY TO A MILLED PART.  THIS CONDITION OBVIOUSLY IS PRESENT IN OTHER LIKE MODELS AND BEECH HAS ACKNOWLEDGED THE PROBLEM IN THEIR PARTS BOOK AS THEY GIVE INSTRUCTIONS FOR ORDERING DIFFERENT PN.  THE NEW PN PARTS ARE MADE FROM .050 INCH ALUMINUM WHILE THE ORIGINAL PARTS WERE MADE FROM .032 INCH ALUMINUM.  THE CRACKS COULD EASILY GO UNDETECTED AND A SB IS NEEDED TO HELP OTHERS FIND AND ELIMINATE THESE CRACKS.                                  1L71 3O      3A15                         
20060825000382006082500038CE  2006       8          25         2006FA0000848    120060822G52803511513022      ANGLE                                   BEECH 36    A36         1151604CE                                                               MLG DOOR        CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL1945MS 360                    E3384                                   DURING A ROUTINE ANNUAL INSPECTION IT WAS FOUND THAT BOTH THE LT AND RT IB GEAR DOOR AFT HINGE ANGLES (P/N'S 35-115130-22, -24, 35-115070-16 AND -18 WERE CRACKED.  IT IS MY OPINION THAT THIS IS DUE TO THE FACT THAT MFG HAS CHANGED THE DESIGN OF THE IB GEAR DOOR FROM A STAMPED ASSY TO A MILLED PART.  THIS CONDITION OBVIOUSLY IS PRESENT IN OTHER LIKE MODELS AND MFG HAS ACKNOWLEDGED THE PROBLEM IN THEIR PARTS BOOK AS THEY GIVE INSTRUCTIONS FOR ORDERING DIFFERENT PN.  THE NEW PN PARTS ARE MADE FROM .050 INCH ALUMINUM WHILE THE ORIGINAL PARTS WERE MADE FROM .032 INCH ALUMINUM.  THE CRACKS COULD EASILY GO UNDETECTED AND A SB IS NEEDED TO HELP OTHERS FIND AND ELIMINATE THESE CRACKS.                                    1L71 3O      3A15                         
20060825000392006082500039CE  2006       8          25         2006FA0000849    120060822G52803511513022      ANGLE                                   BEECH 36    A36         1151604CE                                                               MLG DOOR        CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL1945MS 360                    E3384                                   DURING A ROUTINE ANNUAL INSPECTION IT WAS FOUND THAT BOTH THE LT AND RT IB GEAR DOOR AFT HINGE ANGLES (P/N'S 35-115130-22, -24, 35-115070-16 AND -18 WERE CRACKED.  IT IS MY OPINION THAT THIS IS DUE TO THE FACT THAT MFG HAS CHANGED THE DESIGN OF THE IB GEAR DOOR FROM A STAMPED ASSY TO A MILLED PART.  THIS CONDITION OBVIOUSLY IS PRESENT IN OTHER LIKE MODELS AND MFG HAS ACKNOWLEDGED THE PROBLEM IN THEIR PARTS BOOK AS THEY GIVE INSTRUCTIONS FOR ORDERING DIFFERENT PN.  THE NEW PN PARTS ARE MADE FROM .050 INCH ALUMINUM WHILE THE ORIGINAL PARTS WERE MADE FROM .032 INCH ALUMINUM.  THE CRACKS COULD EASILY GO UNDETECTED AND A SB IS NEEDED TO HELP OTHERS FIND AND ELIMINATE THESE CRACKS.                                    1L71 3O      3A15                         
20060913003982006091300398CE  2006       9          13         2006FA0000851    120060812G323155421029        TORQUE TUBE                             CESSNA500   560CESSNA   2076750CE                                                               NLG DOOR        CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW99     1461                                                           THE NOSE LANDING GEAR DOOR TORQUE TUBE IS CRACKED AT THE WELD THAT ATTACHES THE MOUNTING BRACKET.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA22CE                        
20060915001332006091500133CE  2006       9          15         2006FA0000852    120060712G528055421029        TORQUE TUBE                             CESSNA500   560CESSNA   2076750CE                                                               NOSE GEAR DOORS CRACKED         C      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW99     3016                                                           THE NOSE LANDING GEAR DOOR TORQUE TUBE IS CRACKED AT THE WELD THAT ATTACHES THE MOUNTING BRACKET.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA22CE                        
20060831000022006083100002CE  2006       8          31         2006FA0000853    120060718G323155421029        TORQUE TUBE                             CESSNA500   560CESSNA   2076750CE                                                               NLG DOOR        CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      SW99     4646                                                           THE NOSE LANDING GEAR DOOR TORQUE TUBE IS CRACKED AT THE WELD THAT ATTACHES THE MOUNTING BRACKET.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA22CE                        
20060927000192006092700019CE  2006       9          27         2006FA0000854    120060718G323155421029        TORQUE TUBE                             CESSNA500   560CESSNA   2076750CE                                                               NLG DOORS       CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW99     4182                                                           THE NOSE LANDING GEAR DOOR TORQUE TUBE IS CRACKED AT THE WELD THAT ATTACHES THE MOUNTING BRACKET.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA22CE                        
20060926002512006092600251CE  2006       9          26         2006FA0000855    120060720G323155421029        TORQUE TUBE                             CESSNA500   560CESSNA   2076750CE                                                               NOSE GEAR DOORS DAMAGED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW99                                                                    THE NOSE LANDING GEAR DOOR TORQUE TUBE RECEIVED NEW FROM MFG HAS THE ATTACHMENT ARMS MISALIGNED.  HOLE FOR THE LINKAGE ATTACHMENT BOLT HAS BEEN DRILLED WITH LESS THAN ALLOWABLE EDGE DISTANCE TO COMPENSATE FOR THE MISALIGNED ARMS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F    RTA22CE                        
20060913003972006091300397CE  2006       9          13         2006FA0000856    120060712G323155421029        TORQUE TUBE                             CESSNA500   560CESSNA   2076750CE                                                               NLG DOOR        CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW99     1615                                                           THE NOSE LANDING GEAR DOOR TORQUE TUBE IS CRACKED AT THE WELD THAT ATTACHES THE MOUNTING BRACKET.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA22CE                        
20060927000202006092700020CE  2006       9          27         2006FA0000857    120060718G3240169580001143    LINE                                    BEECH 23    C24R        1151254CE  LYC   O360  IO360A1A    41514EA                              BRAKE SYSTEM    CHAFED          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NE01824BA                       MC533                                   AIRCRAFT LEAKING HYDRAULIC FLUID.  INSP FOUND RT BRAKE LINE  LEAKING APPROX 8 INCHES FWD OF WING SPAR.  FOUND ALUMINUM BRAKE LINE CHAFING AGAINST WIRE REINFORCED HEATING DUCT.  ALSO, EVIDENCE OF CORROSION FROM CONTACT WITH DISSIMILAR METALS.  CUT OFF DAMAGED AREA AND REPLACED WITH NEW MATERIAL AND ON UNION.  ADDED NYLON SPIRAL WRAP FOR CHAFE PROTECTION.  (K)                                                                                                                                                                                                                                                                                                                                                                        1L71 3O3  O  A1CE    1E10                 
20060926002542006092600254GL  2006       9          26         2006FA0000858    120060718G781014836001        MUFFLER                                 CIRRUSSR    SR22        2130001GL  CONT  O550  IO550N      17042SO                              LT, RT EXHAUST  DAMAGED         B  QRQRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW05948AH                       0329                                    LT AND RT MUFFLER FLAME ARRESTERS FOLDED OVER FROM EXHAUST GAS HEAT COMPOUNDED OVER THE 609 HOURS OF THEIR SERVICE LIFE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1L71 3O3  ONTA00009CHE3SO                 
20060828000012006082800001CE  2006       8          28         2006FA0000859    120060817G2720                SERVO                                   CESSNA525   525         2076601CE  WILINTFJ44  FJ44        66000GL                              RUDDER TRIM     MALFUNCTIONED   B      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW99719D 1494                   5250075                                 TECH WAS IN TAILCONE AREA AND NOTICED METAL SHAVINGS UNDER RUDDER SERVO ASSY.  INVESTIGATION REVEALED THAT THE SERVO DRUM  CABLE WAS CUTTING THROUGH THE DRUM GROOVES ARE TO SEVERE SIDE LOADING ON THE CABLE.  SUSPECT THAT THE SEVERE SIDE LOAD CONDITION RESULTED FROM IMPROPER PLACEMENT OF SERVO CABLE TO MAIN SYSTEM CABLE CLAMP.  ROTATION OF THE CLAMP ON THE MAIN RUDDER SYSTEM CABLE INDUCED THE SIDE LOAD.  THIS AC WAS NOT IN FOR AN INSPECTION AND THE TECH FOUND THIS CONDITION BY CHANCE.  (K)                                                                                                                                                                                                                                   1L72 4F4  FRTA1WI    E3GL                 
20060926000712006092600071EA  2006       9          26         2006FA0000860    220060623G8520LW12581         CRANKSHAFT                              PIPER PA31  PA31350     7103110SO  LYC   O540  TIO540J2BD  41532EA                              LT ENGINE       DAMAGED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NE024095L                       318152178   L816261A                    PILOT REDUCED POWER FOR LANDING, PUSHED NOSE OF AC OVER TO DESCEND, LF ENGINE RPM INCREASED.  PULL NOSE OF AC UP, RPM DECREASED.  THEN PILOT REPORTED SLIGHT VIBRATION AND THE BANG.  LT ENGINE WAS SHUTDOWN.   AIRCRAFT LANDED WITHOUT INCIDENT.  INSPECTION OF LT ENGINE WAS PERFORMED AND FOUND THAT THE FRONT 2 CYLINDERS WERE THE ONLY ONES STILL ATTACHED TO THE FRONT THIRD OF THE CRANKSHAFT (THE CRANKSHAFT WAS IN (3) PIECES).  (K)                                                                                                                                                                                                                                                                                                   1L72 3O3  O  A20SO   E14EA                
20060831000032006083100003SO  2006       8          31         2006FA0000861    120060729G2910                HYDRAULIC LINE                          PIPER PA23  PA23250     7102308SO  LYC   O540  IO540*      41532EA                              HYDRAULIC SYS   CHAFED          B      K   NONE                                                                                            K  FLUID LOSS                                                                    NRNOT REPORTED   1                      NE01401PJ                       274112                                  AIRCRAFT SUFFERED HYDRAULIC PRESSURE LOSS, FOUND LT RUDDER CABLE CHAFED THRU PRESSURE LINE BEHIND PILOTS LT SIDE WALL, AREA IS DIFFICULT TO INSPECT DUE TO SIDE WALL/INSULATION.  LINE REPLACE, SYSTEM SERVICED OPERATES NORMAL.  PLEASE FIND BELOW ADDITIONAL ITEMS DISCUSSED IAW TELECOM DATED 8/15/2006.  PROBLEM WITH THE CABLE CHAFING THROUGH THE PRESSURE LINE HAS BEEN IDENTIFIED ONE TIME PREVIOUS TO THIS INCIDENT.  BOTH OCCURRENCES HAPPENED BETWEEN 6000-7000 AC HOURS.  PROBLEM IN BOTH CASES WAS NOT IDENTIFIED UNTIL HYDRAULIC LEAK WAS DETECTED.  MECHANIC REPOSITIONED THE NEW LINE TO ALLEVIATE THE PROBLEM.  (K)                                                                                                            1L72 3O3  O  1A10    1E4                  
20060926000572006092600057SO  2006       9          26         2006FA0000862    120060828G3097                WIRE                                    PIPER PA31T PA31T       7103124SO  PWA   PT6   PT6A28           EA                                              BROKEN          D      CH  ABORTED TAKEOFF         DEACTIVATE SYST/CIRCUITS                                                RN PARTIAL RPM/PWR LOSS      FALSE WARNING                                       TOTAKEOFF        1                      EA35160TR4327                   31T7920036  51943                       RTBETA-LIGHT CAME ON DURING TAKE-OFF ROLL. PROPELLER RPM DROPPED HEAVILY. PULLED CIRCUIT BREAKER. RPM RETURNED TO NORMAL.  FOUND ALL SINGLE WIRE INSULATIONS IN WIRE BUNDLE TOENGINE/PROP SWITCHES, INCLUDING DE-ICE WIRES AT REDUCTION GEAR BOX HARDENED AND BROKEN, MAKING CONTACT.  WIRE BUNDLE RUNS UNDERNEATH EXHAUST FLANGE.  NO OTHER DAMAGE DUE TO FAST PULLING CIRCUIT BREAKER, IF THIS HAPPENS DURING FLIGHT, IT COULD LEAD TO A DANGEROUS SITUATION.  REPLACED ALL WIRING.                                                                                                                                                                                                                                                           1L72 3T4  T  A8EA    E4EA                 
20060922000832006092200083CE  2006       9          22         2006FA0000863    120060718G781015501261        CLAMP                                   CESSNA337   337H        2075732CE  CONT  O360  IO360GB     17025SO                              EXHAUST         CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NE011258S39                     33701894                                WHILE DOING A PRE-TOW WALKAROUND INSPECTION, NOTICED THE FRONT ENGINE EXHAUST TAIL PIPES WERE LOOSE AND SUPPORT CLAMPS PN 15501261 BROKEN ON BOTH LT AND RT SIDES.  BOTH CLAMPS HAD BOTH OUTER EARS BROKEN OFF AT WELDMENT.  PREVIOUS CLAMPS FAILED AFTER EXHAUST SYSTEM OVERHAUL AFTER 191 HOURS.  SUSPECT THAT FAILURES MAY BE DUE TO EXCESS VIBRATION FROM MUFFLE BALL JOINT CLAMPS INSTALLED TOO TIGHTLY.  (K)                                                                                                                                                                                                                                                                                                                              1H72 3O3  O  A6CE    E1CE                 
20060927000052006092700005EA  2006       9          27         2006FA0000864    220060807G7414M3548           ROTOR           SLICK                   PIPER PA28  PA28161     7102803SO  LYC   O320  O320D3G     41508EA                              MAGNETO         BROKEN          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NE039286M           02110612    288616044   RL681539A                   ROTOR SHAFT BROKEN AT CAM SLOT.  REMOVED AND INSPECTED MAGNETO DUE TO 5 PERCENT TIMING DISCREPANCY.  INSTALLED NEW MAGNETO.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L71 3O3  O  2A13    E274                 
20060922000582006092200058SO  2006       9          22         2006FA0000865    120060226G32131180500         STRUT                                   PIPER PA17  PA17        7101702SO  CONT  A65   A65*        17003SO                              LANDING GEAR    DAMAGED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL134879H725                    17178                                   WHEN CHANGING SHOCK CORDS ON THIS AC, NOTICED A DISCOLORATION OF THE INNER STRUT TUBE (LONGER ONE, SUB PN 1180400) AND REMOVED IT FROM THE OUTER TUBE (SHORTER, SUB PN 1180300) ONE OF THE INNER STRUT TUBES WAS CORRODED APPROX 50 PERCENT OF CIRCUMFERENCE.  THE OTHER INNER STRUT HAD MULTIPLE CORROSION HOLES THROUGH ALL THE METAL.  BOTH SHORT TUBES (OUTER) SHOWED OVAL ELONGATION AT THE ENDS INDICATING FLEXING/BENDING OF THE ASSY DURING LANDINGS AND TAKEOFF.  RELATIVELY NEW (HOURS) BUNGEES KEPT THIS GEAR FROM FINAL FAILURE AND RESULTANT GROUND LOOP.  THE BUNGEE CORDS, WHEN INSTALLED, COVER THIS AREA AND ALSO USUALLY HAVE A CLOTH OR ALUMINUM FAIRING OVER THEM.  DETECTION OF THIS REQUIRES REMOVAL OF THE FAIRINGS AT A 1H71 3O3  O  A805    E205                 
20060927000112006092700011CE  2006       9          27         2006FA0000866    120060821G324650300001087     WHEEL                                   BEECH 90    C90A        1152911CE                                                               MLG             CRACKED         B      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA21304TC214                    LJ1719                                  AFTER SEVERAL ATTEMPTS TO FIND SOURCE OF ONGOING TIRE LEAKAGE, WHEEL ASSEMBLY WAS REMOVED FROM AIRCRAFT AND NSPECTED.  FOUND 2 CRACKS OPPOSITE OF (1) OTHER ALONG INNER RADIUS OF INNER WHEEL HALF.  DURING DISASSEMBLY IT WAS NOTED THAT WHEEL ASSEMBLY TIE BOLT NUTS DID NOT HAVE ANY SELF LOCKING FEATURE.  WHEEL WAS ORIGINAL EQUIPMENT WITH ONLY (1) TIRE CHANGE SINCE NEW.  (K)                                                                                                                                                                                                                                                                                                                                                           1L72 3T    RT3A20                         
20060831000042006083100004CE  2006       8          31         2006FA0000867    120060818G2400635A050         SUPPORT BRACKET                         CESSNA525   525         2076601CE  WILINTFJ44  FJ44        66000GL                              ATTENUATOR      CRACKED         B      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL17719D                        5250075                                 FOUND THE LT AND RT ATTENUATOR ACTUATOR LOWER SUPPORT BRACKETS TO BE CRACKED.  THESE BRACKETS HAVE BEEN REPLACED BY ACCOMPLISHMENT OF SB AT PRIOR DATE.  WE HAVE REPEATEDLY FOUND THESE BRACKETS.  CRACKED AGAIN AND AGAIN AFTER THEY ARE REPLACED BY THE SB.  CUSTOMERS OF HAVEING CHANGE THE BRACKETS OVER AND OVER WHEN THE SB WAS SUPPOSED TO BE ADDRESSING THE PROBLEM WITH NEWER, IMPROVED BRACKETS.  RECOMMEND THE OEM STRENGTHEN THE REPLACEMENT BRACKETS.  (K)                                                                                                                                                                                                                                                                         1L72 4F4  FRTA1WI    E3GL                 
20060927000102006092700010CE  2006       9          27         2006FA0000868    120060720G284062266502        SWITCH                                  CESSNA650   650         2076802CE  GARRTTTFE731TFE731*     01518WP                              FUEL LOW LEVEL  MISMANUFACTURED B      O   OTHER                                                                                           W  INADEQUATE Q C                                                                NRNOT REPORTED   1                      GL17993LC                       6500027                                 AFTER ARRIVAL, FOUND FUEL LEAK NEAR IB END OF RT WING.  INVESTIGATION SHOWED THE LOW LEVEL FUEL LIMIT SWITCH WAS NOT ASSEMBLED.  THE FLOAT, PN L15F2, WAS NOT ATTACHED TO THE MOUNT ASSY PN 62266503.  THIS ALLOWED FUEL TO LEAK FROM THE WING.  SWITCH WAS ASSEMBLED, REINSTALLED AND LEAK CHECKED.  NO FURTHER LEAKS NOTED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F4  F  A9NM    E6WE                 
20060831000012006083100001CE  2006       8          31         2006FA0000869    120060315G550035405130        FITTING                                 BEECH 35    35BEECH     1151502CE  CONT  E185  E185*       17014SO                              STABILIZER      CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL274473V4329                   D1291                                   STABILIZER FITTING REMOVED FROM AC TO BE CHECKED IAW AD76-05-04.  DYE PENETRANT INSPECTION REVEALED (2) CRACKS RADIATING FROM THE LOWER BOLT HOLE ATTACHMENT POINTS AS DEPICTED IN DWG.  PROBABLE CAUSE COULD BE FROM IMPROPER TORQUE OF ATTACHMENT BOLTS AT PREVIOUS INSPECTION.  THIS PART IS TO BE INSPECTED EACH 1,000 HRS TIME IN SERVICE.  SUGGEST PROPER TORQUE BE APPLIED DURING INSTALLATION OR UPGRADE OLD FITTING TO THE NEW STYLE FITTING PN 35405130.  (K)                                                                                                                                                                                                                                                                         1L71 3O3  O  A777    E246                 
20060914001962006091400196GL  2006       9          14         2006FA0000870    220060819G732321722           GOVERNOR                                HUGHES369   369E        4470707WP  ALLSN 250C  250C20B     03013GL                              ENGINE          MALFUNCTIONED   D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE07564WP     1003              0564E       CAE837044                   PILOT OBSERVED ENGINE RPM DROOPED TO APPROX 98 PERCENT N2 AND WOULD NOT BEEP UP.  THIS CAUSING LOW ROTOR WARNING TO ILLUMINATE, AS WELL AS AUDIO WARNING TO SOUND.  PILOT ENTERED AN AUTO ROTATION AND OBSERVED THE ENGINE SURGING AS HE APPROACHED THE GROUND.  NORMAL AUTO ROTATION LANDING WAS MADE WITH NO DAMAGE TO AIRCRAFT OR INJURY TO PERSONS.  FOR TROUBLESHOOTING PURPOSE MAINTENANCE CONDUCTED AN ENGINE START AND OBSERVED THE ENGINE WOULD NOT BEEP ABOVE 98 PERCENT N2 AND MINOR SURGING OF THE ENGINE.  MAINTENANCE REPLACED THE PT GOVERNOR.  ENGINE AND AIRCRAFT PERFORMED NORMAL.  AIRCRAFT RETURNED TO SERVICE FOLLOWING OPS FLIGHT CHECK.  (K)                                                                             1G71 3U3  U  H3WE    E4CE                 
20060926001682006092600168EA  2006       9          26         2006FA0000871    220060819G732230804           FLOAT           PRECISION               CESSNA150   152         2071835CE  LYC   O235  O235N2C     41505EA                              CARBURETOR      LEAKING         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM1395429     732   DT21385     15285892                                AIRCRAFT NOTED AS HAVING FUEL DRIPPING FROM BOTTOM COWL, FOUND CAR LEAKING FUEL WHILE SITTING STATIC, REMOVED AND CHECKED CARBURETOR.  DETERMINED (1) OF THE (2) PONTOONS OF THE PLASTIC FLOAT WAS FULL OF FUEL, CONTACT MADE WITH MFG WHO SUGGESTED THEY WERE AWARE OF THE PROBLEM AND HAVE SUPERSEDED THE FLOAT TO A NEWER VERSION, REPLACED THE FLOAT WITH THE 30-864 AND 29-184 FLOAT VALVE CLIP, OPS CHECKED OK.  (K)                                                                                                                                                                                                                                                                                                                      1H71 3O3  ONT3A19    E223                 
20060914000282006091400028EU  2006       9          14         2006FA0000872    120060804G276065WE0103036     PUMP                                    HWKSLYDH1254HS125400F   230145 EU  GARRTTTFE731TFE731*     01518WP                              SPOILERS        FAILED          A  IAVRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP254QB                         25255       84435                       NR 1 HYDRAULIC SYS FAILURE RESULTING IN LOSS OF HYDRAULIC FLUID.  IN FLIGHT DIVERT AFTER DEPARTURE, AFTER ALTERNATE LANDING GEAR/ FLAP EXTNESION.  LT HYDRAULIC SYSTEM PRESSURE LOW LIGHT ILLUMINATED ON TAKEOFF AFTER 80 KTS, CONTINUED TAKEOFF.  AFTER COMPLETING HYDRAULIC FAILURE CHECK LIST, DETERMINED THERE WAS A HYDRAULIC LEAK.  DECLARED AN EMERGENCY AND DIVERTED.  COMPLETED THE HYDRAULIC LOSS CHECKLIST, WHICH BASICALLY INVOLVED PUMPIN GHE LANDING GEAR DOWN AND FLAPS TO POSITION.  LANDED WITHOUT INCIDENT, STOPPED ON THE RUNWAY.  REPLACED 2 PASSENGERS, PINNED THE LANDING GEAR AND TOWED THE AC TO THE FBO RAMP.   (K)                                                                                                    2L72 3F4  FRTA3EU    E6WE                 
20060927000222006092700022CE  2006       9          27         2006FA0000874    120060130G8011PM1201H         STARTER                                 CESSNA172   172M        2072418CE  LYC   O320  O320*       41508EA                              ENGINE          FAILED          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM0170323                       17267200                                PM1201-H STARTER FAILED TO ENGAGE.  INSTALLED DIFFERENT MFG STARTER.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3O3  ONT3A12    E274                 
20060927000292006092700029CE  2006       9          27         2006FA0000878    120060207G8011                PINION GEAR                             CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              STARTER         FAILED          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM01510LP                       172S9510                                PINION GEAR WOULD NOT ENGAGE RING GEAR.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H71 3O3  ONT3A12    1E10                 
20060927000232006092700023CE  2006       9          27         2006FA0000879    120060630G8011                PINION GEAR                             CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              STARTER         FAILED          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM01510LP                       172S9510                                PINION GEAR NOT ENGAGING RING GEAR COMPLETELY.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3O3  ONT3A12    1E10                 
20060922001192006092200119CE  2006       9          22         2006FA0000880    120060830G2821075601011       PLUNGER                                 CESSNA172   172M        2072418CE  LYC   O320  O320*       41508EA                              FUEL STRAINER   SEPARATED       D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO095067H4170                   17265326                                FUEL STRAINER WOULD NOT DRAIN WHEN ACTUATED. INVESTIGATION REVEALED THAT THE RUBBER NIPPLE HAD SEPARATED FROM THE PLUNGER, (P/N 0756010-11). THE FUEL SUMP DRAIN ON THE LT WING ALSO LEAKED AND WAS REPLACED. THE AC HAD RECENTLY BEEN PURCHASED AND IT WAS NOTED THAT AUTO FUEL HAD BEEN USED IN THE PAST. AN STC WAS SECURED AND INSTALL IT ON THE AIRCRAFT. IT IS MY OPINION THAT AN AUTO FUEL WITH ETHANOL ALCOHOL HAD BEEN USED, IN THAT THE PLUNGER NIPPLE WAS (ROCK) HARD AS WAS THE FUEL SUMP DRAIN SEAL. ALL MECHANICS NEED TO MAKE NOTE AS THIS COULD HAVE CAUSED ALL THE FUEL TO LEAK OUT IN FLIGHT AND CAUSED AN OFF FIELD LANDING OR WORSE. IF YOU SMELL AUTO FUEL GO AS DEEP AS NECESSARY TO DETERMINE THE SERVICEABILITY OF THE S1H71 3O3  ONT3A12    E274                 
20060925001652006092500165    2006       9          25         2006FA0000881    220060830G7261537650          COVER                                   BLANCA17    1730A       1220433GL                                                               OIL SUMP        CRACKED         D      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      WP15711LA2100 200               30411                                   5 INCH SPANWISE CRACK, 10 INCHES AFT OF FORWARD EDGE OF OIL SUMP COVER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L71 3O      A18CE                        
20060927000252006092700025EA  2006       9          27         2006FA0000884    220060829G732230804           FLOAT           LYC         MA4SPA105217PIPER PA28  PA28161     7102803SO  LYC   O320  O320D3G     41508EA  SNSNCH74D   74DM        EA  CARBURETOR BOWL FAILED          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE013066H           DC43329     287916219   LW1498739A  A60546          ON SHUTDOWN, THE RPM INCREASED 400 RPM.  ON IDLE, THE ENGINE WOULD IDLE AT 600 RPM, THEN DROP TO 300 RPM THEN DIE.  ON OPENING THE CARBURETOR, HALF OF THE WHITE PLASTIC FLOAT WAS 80 PERCENT FULL OF FUEL.  IT DID NOT LEAK OUT OVER NIGHT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L71 3O3  O  2A13    E274    5  NP88614   
20060913003962006091300396SO  2006       9          13         2006FA0000885    120060812G7820                MUFFLER                                 PIPER PA18  PA18150     7101828SO  LYC   O320  O320*       41508EA                              EXHAUST SYS     CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL034418Z81                     188753                                  DURING ANNUAL INSP FOUND CRACK AT END OF ONE SUPPORT BRACE WITH EVIDENCE OF EXHAUST LEAK.  ADVISED OWNER, HE SAID HE HAD EXPERIENCED EXHAUST LEAKAGE WITH MILD NOSE AND LEAKAGE.   REPAIRED MUFFLER AND RETURNED TO US AND MUFFLER WAS REINSTALLED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1H71 3O3  O  1A2     E274                 
20060913002582006091300258    2006       9          13         2006FA0000886    120060830G8011                STARTER                                                                                                                                 ENGINE          FAILED          B  WS9RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM07     45                                                             STARTER, WILL NOT SPIN ON LOAD.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           
20060922000892006092200089EU  2006       9          22         2006FA0000887    120060815G7797                CONNECTOR                               SNIAS 350   AS350BA     8680817EU  TMECA ARRIELARRIEL1B    6OO30NE                              TORQUE IND      CONTAMINATED    B  HXSRA   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CRCRUISE         1                      AL0557954                       1127        501                         DEPARTED BASE, HEADED FOR THE GLACIER, EN ROUTE THE PILOT NOTICED HIS TORQUE READING WAS FLUCTUATING.  THE PILOT RETURNED TO BASE AND THE MECHANIC FOUND THAT THE ENGINE DECK PLUG HAD WATER IN IT FROM THE HEAVY RAINS WE HAVE BEEN ENDURING.  THE MECHANIC CLEANED OUT THE PLUG AND THE AIRCRAFT WAS RETURNED TO SERVICE AFTER AN OPERATIONS CHECK WAS COMPLETED.  (K)                                                                                                                                                                                                                                                                                                                                                                        1G71 3U3  UNCH9EU    E19EU                
20060913003842006091300384EA  2006       9          13         2006FA0000888    120060608G6210234R0001        BLADE                                   BOEING234   234         1385049EA                                                               MAIN ROTOR      DEBONDED        B  CHIRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM09CFHFB                       MJ005                                   ROTOR BLADE HAD A LARGE SKIN DEBOND ON THE LOWER SURFACE FROM THE TRIM TAB OB, BETWEEN STA 227 AND STA 329, APPROXIMATELY 475-500 SQUARE INCHES (ALLOWABLE REPAIR LIMITS ARE 20 INCHES SPAN WISE AND 13 INCHES CHORD WISE.  UNBONDED SKIN WAS REMOVED TO EXPOSE HONEYCOMB CORE FOR INSPECTION.  HONEYCOMB WAS OIL FREE AND APPEARED TO BE IN GOOD CONDITION.  THE ROTOR BLADE WILL UNDERGO FURTHER INVESTIGATION TO DETERMINE THE PROBABLE CAUSE AND REPAIR SCHEME IF POSSIBLE.  THE MANUFACTURER HAS BEEN NOTIFIED.  (K)                                                                                                                                                                                                                       2G72 4U      H9EA                         
20060913003952006091300395GL  2006       9          13         2006FA0000889    120060829G7920                UNION                                   AMTR  LANCARLC41550FG   5150001GL  CONT  O550  TSIO550C         SO                              ENGINE          CRACKED         D      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      NM09999GL251                    41034       802678                      THE AN911-1J UNION THAT SUPPLIES OIL TO THE OIL PRESSURE TRANSDUCER, THE HOBBS PRESSURE SWITCH, AND THE OIL FEED LINE, AT THE BASE OF THE OIL COOLER, ON THE BACK OF THE ENGINE, WAS CRACKED AT THE PIPE THREADS, AND THEN BROKE IN THE PROCESS OF REMOVING THE PART.  THE WEIGHT OF THE FITTINGS ATTACHED TO THE UNION HANGING OUT AS FAR AS THEY ARE, AND THE VIBRATION OF THE ENGINE, MAY HAVE CAUSED THE UNION TO CRACK AT THE PIPE THREADS.  THE HARDNESS OF THE STAINLESS STEEL PART COULD ALSO HAVE BEEN PART OF THE PROBLEM.  THE AC WAS SCHEDULED THAT DAY BUT AN OIL LEAK WAS NOTICED AND INVESTIGATED BEFORE THE FLIGHT, WHICH WOULD HAVE ENDED WITH A CATASTROPHIC FAILURE OF THE ENGINE DUE TO OIL LOSS.  THE TEMPORARY RECOMMENDAT1L71 3O3  ORTEXPA1L71E5SO                 
20060913003642006091300364CE  2006       9          13         2006FA0000890    120060824G2730                CONTROL CABLE                           BEECH 90    C90A        1152911CE  PWA   PT6   PT6A21      52043EA                              ELEVATOR        OUT OF ADJUST   B  E81RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03405DD                       LJ1748                                  DURING 1ST SCHEDULED PHASE 1 AND PHASE 2 INSPECTIONS NOTED ELEVATOR CONTROL SYSTEM CABLE TENSIONS OUT OF MM SERVICE LIMITS.  FOUND ELEVATOR NEUTRAL POSITIONS OUT OF LIMITS FOLLOWING CABLE TENSION ADJUSTMENTS (WITH FORWARD AND AFT RIG PINS INSTALLED).  FOUND FORWARD BELLCRANK DOWN STOP BOLT CLEARANCE PAST SERVICE LIMIT AND ADJUSTED.  FOUND ELEVATOR BOBWEIGHT CLEARANCE GAP EXCESSIVE.  REQUIRED ADJUSTING THE  FORWARD PUSHROD ASSY AND ADDING WASHERS TO OBTAIN BOBWEIGHT CLEARANCE WITHIN SERVICE LIMITS.  AIRCRAFT HAD BEEN SUBJECT TO SPECIAL FLIGHT CONTROL SYSTEM INSPECTION FOLLOWING MANUFACTURE LOGBOOK RECORDS.  RECOMMEND FOLLOW-UP INVESTIGATION BY MFG ON OTHER AC.  (K)                                                1L72 3T4  TRT3A20    E4EA                 
20060927000432006092700043CE  2006       9          27         2006FA0000891    120060824G33508751062         POWER SUPPLY                            BEECH MU300 400A        1155402CE                                                               EMERGENCY LIGHTSINOPERATIVE     B  E81RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL0345RK 3957                   RK43                                    DURING SCHEDULED 12 MONTH/200 HR INSPECTION OF AIRCRAFT SERVICES EMERGENCY LIGHTING SYS INSTALLED UNDER STS ST00344AT FOUND AFT POWER INSTALLED UNDER STC ST00344AT FOUND AFT POWER SUPPLY TO HAVE NO OUTPUT.  VERIFIED POWER SUPPLY RECEIVING BATTERY CHARGING VOLTAGE AND BATTERY FULLY CHARGED.  REPLACED POWER SUPPLY WITH NEW UNIT, SYSTEM TESTS SATISFACTORY IAW MANUAL INSPECTION GUIDE.  (K)                                                                                                                                                                                                                                                                                                                                            2H72 4F    RTA16SW                        
20060913003622006091300362    2006       9          13         2006FA0000892    420060824G22156225735002      MOUNT                                   BEECH 90    C90A        1152911CE  PWA   PT6   PT6A21      52043EA                              RUDDER SERVO    DISTORTED       B  E81RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03405DD201                    LJ1748                                  DURING FIRST SCHEDULED 1ST AND 2ND PHASE INSPECTIONS NOTED SQUEAKING AND METAL TO METAL CONTACT NOISES WHEN RUDDER MOVED SIDE TO SIDE.  FOUND RUDDER SERVO CABLE RUBBING ON SMT-65 SERVO MOUNT CABLE DRUM COVER.  REPLACED SMT-65 UNIT AND REINSTALLED, RIGGED SERVO CABLE.  RUDDER OPERATIONS NOW NORMAL, AUTOPILOT OPERATIONAL CHECKS OK.  SUSPECT SMT -65 SERVO MOUNT EITHER DISTORTED FROM PRIOR HANDLING OR NOT ASSEMBLED CORRECTLY.  (K)                                                                                                                                                                                                                                                                                                  1L72 3T4  TRT3A20    E4EA                 
20060913003632006091300363CE  2006       9          13         2006FA0000893    120060824G2720                FASTENER                                BEECH 90    C90A        1152911CE  PWA   PT6   PT6A21      52043EA                              RUDDER SYS      OVERTORQUED     B  E81RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL03405DD                       LJ1748                                  FOUND OTHER LT SIDE RUDDER CONTROL ATTACHING HARDWARE TIGHT OR OVERTIGHTENED.  EXAMINED LT RUDDER CONTROL SYSTEM HARDWARE FOR SERVICEABILITY AND REINSTALLED AS REQUIRED WITH NORMAL RECOMMENDED TORQUES, ADJUSTED INTERCONNECT ROD AS REQUIRED WITH NORMAL RECOMMENDED TORQUES, ADJUSTED INTERCONNECT ROD AS REQUIRED.  REPLACED PILOT`S OB PUSHROD ASSY BEARINGS AND REINSTALLED.  NOSEWHEEL STEERING AND RUDDER OPERATIONS FOUND NORMAL AFTER REASSEMBLY.  SUSPECT HARDWARE POSSIBLY OVERTIGHTENED DURING INITIAL AC ASSY, AIRCRAFT WAS ALSO SUBJECT TO SPECIAL FLIGHT CONTROL SYSTEM INSPECTION FOLLOWING MFG.  RECOMMENDED FURTHER INVESTIGATION BY MFG TO DETERMINE IF A ONE-TIME SB.  (K)                                                1L72 3T4  TRT3A20    E4EA                 
20060913003612006091300361CE  2006       9          13         2006FA0000894    120060824G2720139909B47       BOLT                                    BEECH 90    C90A        1152911CE  PWA   PT6   PT6A21      52043EA                              RUDDER SYS      OVERTORQUED     B  E81RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03405DD                       LF1748                                  DURING 1ST SCHEDULED PHASE 1 AND PHASE 2 INSPECTION INVESTIGATED PILOT COMPLAINT OF STIFF NOSEWHEEL STEERING.  VERIFIED COMPLAINT, FOUND NOSEWHEEL STEERING STIFF AND LOUD POPPING NOISES COMING FROM COCKPIT UNDER FLOOR AREA WHEN TAXIED FROM COPILOTS POSITION.  ACCESSED COCKPIT AREA RUDDER CONTROL SYSTEM AND FOUND PILOTS SIDE OB RUDDER CONTROL PUSHROD TO HAVE EXCESSIVE PLAY.  UPON REMOVING OB PUSHROD ASSY.  BEARINGS FELL OUT OF ROD END BEARING ASSY.  FURTHER INVESTIGATION SHOWED PN 50-5244553 LT SIDE RUDDER BELLCRANK ASSY OPERATION TIGHT, FOUND  PN 139909B47 PIVOT BOLT OVERTIGHTENED.  ALSO FOUND LT TO RT RUDDER CONTROLS INTERCONNECT TUBE ATTACHING HARDWARE OVERTIGHTENED.  (K)                                      1L72 3T4  TRT3A20    E4EA                 
20060914001522006091400152EU  2006       9          14         2006FA0000896    220060824G72501975M84P01      RETAINER                                BOEING737   737400      138449ANM  CFMINTCFM56 CFM563C1    13802EU                              ENGINE          DISLODGED       W  QEMYO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA35SPLKC29341                              857849                      (REF: 2006FA00008996) DURING STRIP OF ENGINE 857819 FOR SCHEDULED LLP REPLACEMENT IT WAS NOTED THAT THE HPT FORWARD BLADE RETAINER HAD LIBERATED 2 SECTIONS OF MATERIAL, ONG 3.5 INCHES X .8750 INCH AND 1) 2 INCH X .8750 INCH.  THE LIBERATED MATERIAL HAD CAUSED MINOR LPT AND HPT IMPACT DAMAGE.  MFG HAS BEEN ASKED TO INVESTIGATE THIS DEFECT.  (K)                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F4  FRTA16WE   E21EU                
20060913003942006091300394EA  2006       9          13         2006FA0000897    220060825G8530AEL65102        CYLINDER                                CESSNA172   172N        2072434CE  LYC   O360  O360A4M     41514EA                              ENGINE          SEPARATED       D      E   ENGINE SHUTDOWN                                                                                 O  OTHER                                                                         NRNOT REPORTED   1                      EA21733EN206                    17268239                                PILOT EXPERIENCED A NOTICEABLE POP SOUND IN ENGINE COMPARTMENT FOLLOWED BY ROUGHNESS.  SOON AFTER THE ENGINE OIL PRESSURE STARTED TO DETERIORATE AND PILOT ELECTED TO SHUTDOWN ENGINE AND STOPPED PROPELLER FROM TURNING BY PUTTING AIRCRAFT IN NOSE HIGH ATTITUDE.  HE MANAGE TO GLIDE TO MAJOR AIRPORT AND DEAD STICK LAND SUCCESSFULLY WITHOUT ACCIDENT.  INVESTIGATION SHOWED THAT THE NR 1 CYLINDER HEAD SEPARATED FROM BARREL.  THIS CYLINDER WAS REPLACED 206 HOURS PRIOR WHEN ENGINE WAS OVERHAULED.  THE CYLINDER WAS PURCHASED NEW.  NEW CYLINDER WAS INSTALLED AND ENGINE RAN NORMALLY WITH NO ADVERSE PROBLEMS NOTED.  THE SEPARATION OF CYLINDER IS THOUGHT TO BE STRESS CRACKING DUE TO THREADS CUT IN CYLINDER HEAD HAVING LITTLE1H71 3O3  ONT3A12    E286                 
20060913003992006091300399GL  2006       9          13         2006FA0000898    120060818G321321410103        AXLE                                    BOMBDRBD700 BD7001A10   1390006GL                                                               LT MLG          CORRODED        B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NE03700ML2175                   9043                                    LT MLG TRAILING ARM AXLE FOUND TO HAVE CORROSION ON TAPERED WASTELAND AREAS AT BOTH WHEEL POSITIONS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F    RTT00003NY                     
20060913003932006091300393SW  2006       9          13         2006FA0000899    120060809G3230ED10055         BOLT                                    GULSTM690TP 690C        7630517SW  GARRTTTPE331TPE331*     01514WP                              NLG             SHEARED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM09777NV4937                   11680                                   DURING ROUTINE INSPECTION FOUND NOSE GEAR LOWER DRAG BRACE BOLT SHEARED AT JUNCTION OF REDUCED DIAMETER BOLT HAD NOT YET CAME OUT OF ITS BORE AND THEREFORE THE GEAR DID NOT COLLAPSE.  BUT IT WAS READY TO.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1H72 3T3  T  2A4     E2WE                 
20060925001602006092500160WP  2006       9          25         2006FA0000900    120060901G6720HS10537         CABLE                                   HILLERUH12  UH12E       4360122WP                                                               TAIL ROTOR      BROKEN          G      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         AGAGRICULTURE    1                      SW118402D250                    1093                                    LT TAIL ROTOR CABLE FAILED. OPERATOR OPERATES IN VERY DUSTY ENVIRONMENT. BUILD UP OF DUST AND OILY SUBSTANCE FROM PRODUCT FOR SPRAYING CAUSE A FINE ABRASIVE SUBSTANCE ON CABLES AT PULLEYS. CABLE NEEDS PROTECTION FROM ENVIRONMENT AND MORE FREQUENT INSPECTION AND/OR REPLACEMENT.                                                                                                                                                                                                                                                                                                                                                                                                                                                           1G71 3O      4H11                         
20060915000202006091500020CE  2006       9          15         2006FA0000901    120060912G24971N6391          DIODE           CESSNA                  CESSNA172   172S        2072439CE                                                               BUSS BAR        FAULTY          B      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      SO15452ER48   48                172S10255                               ON A RECENT LOCAL FLIGHT, ONE OF THESE AIRCRAFT EXPERIENCED THE LOSS OF THE MFD, OR RT DISPLAY AS WELL AS THE COMM 2, NAV 2, AUDIO PANEL AND TRANSPONDER. THE CREW ELECTED TO MAKE A PRECAUTIONARY LANDING AT THE NEAREST AIRPORT. ON INSPECTION, IT WAS DISCOVERED THAT THE POWER TO BUSS 2 WAS NOT PRESENT. THE BUSS 2 CIRCUIT BREAKER WAS REPLACED AND THE SYSTEM FUNCTIONED PROPERLY. SHORTLY AFTER, THE MFD FAILED AGAIN. AFTER CLOSER INSPECTION THE WIRE PROVIDING POWER TO THE MFD BREAKER WAS FOUND LOOSE ON THE TERMINAL. THIS WIRE WAS SECURED AND THE AIRCRAFT INCURRED NO FURTHER PROBLEMS. A FLEET INSPECTION OF THE BUSS WIRING FOR THE ESSENTIAL BUSS, BUSS 1 AND BUSS 2 WAS COMMENCED. ADDITIONAL LOOSE WIRE TERMINALS WERE FOU1H71 3O    NT3A12                         
20060926000502006092600050SO  2006       9          26         2006FA0000902    220060729G8530649543          CYLINDER                                CESSNA175   175A        2072504CE  CONT  O300  GO300*      17022SO                              ENGINE          SEPARATED       G      A   UNSCHED LANDING                                                                                 D  INFLIGHT SEPARATION                                                           CRCRUISE         1                      GL116793E3    3                 56293       121479C                     NR (5) CYLINDER SEPARATED FROM THE CRANK-CASE IN FLIGHT RESULTING IN ENGINE FAILURE AND AN UN-PLANNED, SAFE LANDING OF THE AIRCRAFT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H71 3O3  O  3A17    E298                 
20060918000102006091800010CE  2006       9          18         2006FA0000903    120060913G24971N6391          DIODE                                   CESSNA172   172S        2072439CE                                                               NR 1 BUSS       LOOSE           B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15465ER38                     172S10290                               THIS OPERATOR HAS A FLEET OF 16 CESSNA 172S NAVIII AIRCRAFT.  DUE TO SOME OPERATIONAL DIFFICULTIES WHERE BUSS WIRING DISCREPANCIES WERE FOUND, A FLEET WIDE INSPECTION OF THE BUSS WIRING, TERMINAL CONNECTIONS AND WIRE ROUTING WAS ACCOMPLISHED.  THE FOLLOWING WAS FOUND ON THIS AIRCRAFT: REMOVED CIRCUIT BREAKER PANEL AND FOUND LOOSE WIRES COMING FROM DIODES, GOING TO DIFFERENT CIRCUIT BREAKER BUSSES.  TIGHTENED LOOSE NUTS AND CHECKED ALL OTHER WIRE CONNECTIONS, NONE NOTED.  REMOVED SPARE WIRES LOOPED THRU OPEN BREAKER MOUNTING HOLE AND SECURED TO WIRE BUNDLE.  CHECKED J-BOX FOR LOOSE CONNECTIONS, NONE NOTED.  REINSTALLED BREAKER PANELS AND SECURED ALL WIRES AND FITTINGS.                                            1H71 3O    NT3A12                         
20060921002492006092100249EA  2006       9          21         2006FA0000904    220060914G7313LW15472         PUMP                                    PIPER PA28  PA28180     7102808SO  LYC   O360  O360A3A     41514EA                              FUEL SYSTEM     LEAKING         P      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL037103W2900                   28890       L505536                     UPON RETURNING FROM A TRAINING FLIGHT, A FAINT SMELL OF GAS WAS NOTED. SINCE THE ELECTRIC PUMP WAS ON, IT WAS TURNED OFF.  NO ENGINE PERFORMANCE PROBLEMS WERE NOTED AND LANDING WAS NORMAL. UPON LANDING IT WAS NOTICED THAT FLUID WAS DRAINING FROM THE FUEL PUMP VENT LINE.  THIS APPEARED TO BE A MIX OF GAS AND OIL. IT IS ESTIMATED 3-4 QUARTS DRAINED FROM THE VENT BEFORE STOPPING. THE OIL PAN WAS DRAINED AND WAS FOUND TO CONTAIN 8-10 QUARTS OF GAS/OIL MIX. THE OIL FILTER WAS OPENED AND NO METAL WAS FOUND. THE OLD PUMP HAS NOT YET BEEN OPENED AND WAS OPERATING SUFFICIENTLY FOR THE ENGINE TO RUN, BUT IT IS PRESUMED THE PUMP DIAPHRAGM HAD RUPTURED CAUSING FUEL TO LEAK INTO THE ENGINE CRANKCASE. NO EVIDENCE OF THE PUMP1L71 3O3  O  2A13    E286                 
20060922000422006092200042EA  2006       9          22         2006FA0000905    220060914G7314                DIAPHRAGM       AC                      PIPER PA28  PA28180     7102808SO  LYC   O360  O360A3A     41514EA                              FUEL PUMP       RUPTURED        P      O   OTHER                                                                                           KB FLUID LOSS                SMOKE/FUMES/ODORS/SPARKS                            NRNOT REPORTED   1                      GL037103W                       28890       L505536                     UPON RETURNING FROM A TRAINING FLIGHT, A FAINT SMELL OF GAS WAS NOTED. SINCE THE ELECTRIC PUMP WAS ON, IT WAS TURNED OFF.  NO ENGINE PERFORMANCE PROBLEMS WERE NOTED AND LANDING WAS NORMAL. UPON LANDING IT WAS NOTICED THAT FLUID WAS DRAINING FROM THE FUEL PUMP VENT LINE.  THIS APPEARED TO BE A MIX OF GAS AND OIL. IT IS ESTIMATED 3-4 QUARTS DRAINED FROM THE VENT BEFORE STOPPING. THE OIL PAN WAS DRAINED AND WAS FOUND TO CONTAIN 8-10 QUARTS OF GAS/OIL MIX. THE OIL FILTER WAS OPENED AND NO METAL WAS FOUND. THE OLD PUMP HAS NOT YET BEEN OPENED AND WAS OPERATING SUFFICIENTLY FOR THE ENGINE TO RUN, BUT IT IS PRESUMED THE PUMP DIAPHRAGM HAD RUPTURED CAUSING FUEL TO LEAK INTO THE ENGINE CRANKCASE. NO EVIDENCE OF THE PUMP1L71 3O3  O  2A13    E286                 
20060927000282006092700028SO  2006       9          27         2006FA0000906    220060823G8520TCM536379       BOLT                                                                       CONT  O550  TSIOL550A        SO                              CRANKSHAFT GEAR SHEARED         B  VA1RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW19     58                                 800554                      CRANKSHAFT GEAR BOLTS SHEARED/BROKE CAUSING ENGINE FAILURE.  (ENGINE FIALED ON GROUND, DURING STARTING) (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            3  O          E4SO                 
20060927000302006092700030CE  2006       9          27         2006FA0000907    120060822G323099100023        MOTOR                                   CESSNA310   310Q        2074242CE  CONT  O470  IO470*      17026SO                              MLG             FAILED          B  E81RL   ABORTED APPROACH                                                                                J  WARNING INDICATION                                                            APAPPROACH       1                      GL037940Q                       310Q0623                                LANDING GEAR WOULD NOT EXTEND ELECTRICALLY ON APPROACH.  OPERATIONS NORMAL WHEN LANDING GEAR EXTENDED WITH MANUAL EMERGENCY EXTENSION SYS. FOUND LANDING GEAR ACTUATOR MOTOR INOPERATIVE.  WOULD MAKE NOISE BUT NOT ROTATE.  REPLACED MOTOR WITH OVERHAULED REPLACEMENT UNIT; LANDING GEAR SYS OPERATIONS NORMAL.  CLEANED CORROSION FROM BATTERY TERMINALS, SUSPECT VOLTAGE DROP UNDER  LANDING GEAR OPERATIONS LOAD MAY HAVE CONTRIBUTED.  TRANSIENT AC, RECORDS NOT AVAILABLE TO VERIFY MOTOR TIME IN SERVICE.  (K)                                                                                                                                                                                                                          1L72 3O3  O  3A10    E1CE                 
20060926002382006092600238CE  2006       9          26         2006FA0000908    120060817G3230MS250261        SWITCH                                  BEECH 36    B36TC       1151609CE  CONT  O520  GTSIO520*   17032SO                              MLG             FOULED          B  E81RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL03515EK                       EA440                                   LANDING GEAR WOULD NOT EXTEND ELECTRICALLY UPON APPROACH TO RFD.  MANUAL EXTENSION OPERATIONS NORMAL.  TROUBLESHOT LANDING GEAR ELECTRICAL SYS.  FOUND S45 LANDING GEAR ACTUATOR DYNAMIC BRAKE DOWNLIMIT SWITCH OIL SOAKED AND FOULED BY LINT, FUZZ, ETC.  CLEANED DOWNLIMIT SWITCH AS REQUIRED AND CYCLED LANDING GEAR ELECTRICALLY; OPERATION NORMAL.  SUSPECT OIL AND LINT BLOCKING FULL SWITCH TRAVEL AND/OR CAUSING HIGH RESISTANCE IN S45 SWITCH.  DYNAMIC BRAKE LIMIT SWITCHES SHOULD BE INSPECTED CLOSELY AND CLEANED IF REQUIRED EACH 100 HR OR ANNUAL INSPECTION.  THIS AREA CAN BE PRONE TO ATTRACTING DIRT AND UPHOLSTERY (FUZZ).  (K)                                                                                              1L71 3O3  O  3A15    E7CE                 
20060927000262006092700026GL  2006       9          27         2006FA0000909    120060907G7120                BELT                                    AMTR  WOODY WOODYPUSHER        GL  CONT  A65   A65*        17003SO                              REDUCTION BRACK FRACTURED       D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP1956JH 191                    JEH2                                    ULTRALIGHT FRACTURED ENGINE BELT REDUCTION BRACKET CAUSING IN-FLIGHT SHUTDOWN AND EMERGENCY LANDING.  PROBABLE CAUSE: ENGINE BELT REDUCTION BRACKET STRESS/FATIGUE CRACK CAUSING HEAVY ENGINE VIBRATION AND SHUTDOWN.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1H71 3O3  O  EXPA1H71E205                 
20060927000242006092700024CE  2006       9          27         2006FA0000910    120060626G3000991240217       SHUTOFF VALVE                           CESSNA650   650         2076802CE  GARRTTTFE731TFE731*     01518WP                              ANTI-ICE SYS    MISINSTALLED    B  EBVRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE09993LC                       6500027                                 DETERMINED THE PRESSURE REGULATOR SHUTOFF VALVE WAS LEAKING.  FOUND THE REGULATOR HAD BEEN INSTALLED WITHOUT GASKETS.  THE PARTS MANUAL DOES NOT CLEARLY IDENTIFY THAT GASKETS ARE REQUIRED TO BE INSTALLED WITH THIS SPECIFIC PN OF VALVE.  CONTACTED AND CONFIRMED THAT GASKET PN 24096-150C IS REQUIRED TO BE INSTALLED ON THIS VALVE.  MAINTENANCE PERSONNEL INSTALLED GASKETS, PERFORMED LEAK CHECK, AND DETERMINED LEAKAGE PROBLEM HAD BEEN CORRECTED BY INSTALLATION OF GASKETS.  (K)                                                                                                                                                                                                                                                    2L72 4F4  F  A9NM    E6WE                 
20060927000332006092700033EA  2006       9          27         2006FA0000911    220060828G7314RGRG0957OK1     PUMP                                    GROB  120   G120A       1660208EU  LYC   O540  AEIO540D4D5      EA                              ENGINE FUEL     LEAKING         B  VJ3RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP07862AF788                    85002       RL2155648A                  PILOT REPORTED A STRANGE ODOR AFTER THEY PUT THE GEAR UP, WHILE TROUBLESHOOTING MECHANIC FOUND ENGINE FUEL PUMP LEAKING FROM PRESSURE ADJUSTMENT SCREW.  NO PROPABLE CAUSE OR RECOMMENDATIONS AT THIS TIME.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L71 3O3  ORTA49CE   1E4                  
20060927000212006092700021CE  2006       9          27         2006FA0000912    120060817G3610AA3216CW        SHAFT                                   BEECH 33    F33A        1151425CE  CONT  O520  IO520BB     17032SO                              AIR PUMP        SHEARED         B  VJ3RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP078240T173                    CE1542      830141R                     PILOT REPORTED INSTRUMENT AIR PRESSURE WENT TO -0- IN FLIGHT, PILOT THEN SELECTED STANDBY PUMP AND RETURNED TO BASE.  UP ON TROUBLESHOOTING THE MECHANIC REMOVED THE AIR PUMP AND FOUND THE SHAFT WAS SHEARED.  NO PROBABLE CAUSE OR RECOMMENDATIONS AT THIS TIME.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L71 3O3  O  3A15    E5CE                 
20060927000322006092700032CE  2006       9          27         2006FA0000913    120060817G3610AA3216CW        SHAFT                                   BEECH 33    F33A        1151425CE  CONT  O520  IO520BB     17032SO                              AIR PUMP        SHEARED         B  VJ3RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP078240T173                    CE1542      830141R                     PILOT REPORTED INSTRUMENT AIR PRESSURE WENT TO -0- IN FLIGHT, PILOT THEN SELECTED STANDBY PUMP AND RETURNED TO BASE.  UPON TROUBLESHOOTING, THE MECHANIC REMOVED THE AIR PUMP AND FOUND THE SHAFT WAS SHEARED.  NO PROBABLE CAUSE OR RECOMMENDATIONS AT THIS TIME.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L71 3O3  O  3A15    E5CE                 
20060927000372006092700037NE  2006       9          27         2006FA0000914    220060821G72613035890         TRANSFER TUBE                           BEECH 90    F90         1152909CE  PWA   PT6   PT6A135     52043NE                              ENGINE OIL      CHAFED          B  BNGRO   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  NRNOT REPORTED   1                      GL19234CW                       LA236       PCE35079                    IN FLIGHT NOTICED TORQUE METER WAS UNSTABLE, CHECKED OIL PRESSURE AND SAW IT DROPPING.  REDUCED POWER TO IDLE OIL PRESSURE WAS IN YELLOW RANGE.  SHUTDOWN ENGINE AND LANDED.  REMOVED FRONT COWLING AND FOUND INLET DEICE TUBE HAD RUBBED A HOLE IN THE OIL PRESSURE TRANSFER TUBE RT SIDE ON ENGINE.  CHECKED CHIP DETECTOR CHECKED OK.  CHECKED OIL FILTER CHECKED OK.  REMOVED AND REPLACED TUBE AND RELOCATED DEICE TUBE.  SERVICED OIL SYSTEM AND GROUND RUN RECHECKED CHIP DETECTOR AND FILTER CHECKED OK.  RECOMMEND THAT BEFORE FRONT TOP COWLING IS INSTALLED THAT DEICE TUBES BE CHECKED FOR CLEARANCE AT OTHER ITEMS IN COWLING.  (K)                                                                                                1L72 4T4  T  A31CE   E4EA                 
20060927000152006092700015NM  2006       9          27         2006FA0000915    120060802G3232273T61027       CYLINDER        BOEING                  BOEING767   767*               NM                                                               ACTUATOR        DAMAGED         B  IU6RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM01          33938 SHL1262                                             (REF NR: 209609/QN1) PIN HOLE THROUGH CYLINDER WALL.  PRESSURES CYCLES AND MATERIAL DEFECT. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F    RTA1NM                         
20060927000442006092700044NM  2006       9          27         2006FA0000916    120060802G291365447822        HOUSING                                 BOEING737   737*               NM                                                               HYD PUMP        CRACKED         B  IU6RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM01                                                                    (REF NR 209606/PH30) CRACK IN HOUSING.  CYCLICAL FATIGUE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F    RTA16WE                        
20060926001342006092600134SO  2006       9          26         2006FA0000917    220060906G8520653631          GEAR                                    CESSNA206   U206F       2073333CE  CONT  O520  IO520F      17032SO  MCAULYD3A34 D3A34C401   GL  CRANKSHAFT      BROKEN          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NE058411Q167                    U20603271   830575R     011026          AC FLEW A SHORT LEG TO AN ISLAND 25 NM OFFSHORE.  AFTER START-UP THE PILOT HEARD AN UNUSUAL NOISE THAT SOUNDED LIKE A LOOSE VALVE TRAIN.  THE PILOT QUICKLY SHUT THE POWERPLANT DOWN AND DECIDED IT WOULD NOT BE SAFE TO COMPLETE THE TRIP BACK TO MAINLAND.  MECHANIC FLEW OUT TO THE ISLAND TO DETERMINE THE SOURCE OF THIS UNUSUAL NOISE.  FURTHER INVESTIGATION REVEALED THAT THE SOURCE OF THE NOISE WAS 2 TEETH BROKEN OFF OF THE CRANKSHAFT GEAR.  THE IDLER GEAR AND THE STARTER ADAPTER GEAR WERE ALSO DAMAGED AS A RESULT OF THE INTERACTION WITH THE DAMAGED CRANKSHAFT GEAR.  THE TEETH THAT WERE BROKEN OFF HAVE NOT BEEN LOCATED.  METAL SLIVERS AND PIECES WERE ALSO IDENTIFIED IN THE AREA AND OIL.  THIS IS PRELIMINARY INFORMA1H71 3O3  O  A4CE    E5CE    5  CP47GL    
20060921002462006092100246CE  2006       9          21         2006FA0000918    120060913G2497                JUMPER                                  CESSNA172   172S        2072439CE                                                               CB PANEL        LOOSE           B      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      SO15458ER15                     172S10258                               DURING INSPECTION OF THE BUS WIRING, THE JUMPER WIRE BETWEEN THE ESSENTIAL BUS AND THE BUS 1 CONNECTION WAS FOUND LOOSE. THE REMAINDER OF THE SCREWS OF THOSE CIRCUIT BREAKERS WERE CHECKED FOR SECURITY, AND SEVERAL WERE FOUND SLIGHTLY LOOSE REQUIRING .2500 TURN OR MORE TO SECURE THEM.                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H71 3O    NT3A12                         
20060921002522006092100252CE  2006       9          21         2006FA0000919    120060911G24971N6391          DIODE                                   CESSNA172   172S        2072439CE                                                               ELECTRICAL      LOOSE           B      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      SO15461ER34                     172S10281                               DURING INSPECTION OF THE BUSS STRIPS, THE 2 DIODES FOR THE ALT AND WARNING CIRCUIT BREAKERS WERE FOUND LOOSE AT THEIR ATTACH POINTS TO THE BUS. THE ATTACHING HARDWARE  (NUTS) WERE SEVERAL COMPLETE TURNS FROM BEING SECURE, OR ABOUT THE WIDTH OF THE NUT GAP SHOWING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1H71 3O    NT3A12                         
20060926000292006092600029    2006       9          26         2006FA0000922    420060915G23301F220100102     AMPLIFIER                               BOEING737   737*               NM  GE    CFM56 CFM56*      13802NE                              ENTERTAIN SYS   FIRE            C      H   DEACTIVATE SYST/CIRCUITS                                                                        AB FLAME/FIRE                SMOKE/FUMES/ODORS/SPARKS                            TXTAXI/GRND HDL  1                      EA17367G                        28579                                   WHILE MAINTENANCE PERSONNEL WERE PERFORMING A ROUTINE POST FLIGHT INSPECTION, A TECHNICIAN DISCOVERED A PROBLEM.  ACFT POWERED BY EXTERNAL POWER, AND CABIN ENTERTAINMENT SYS OPERATING (PLAYING A DVD MOVIE) WITH THE AUDIO SYSTEM VOLUME AT A LOW LEVEL.  AFTER A FEW MINUTES OF OPERATION, A TECHNICIAN NOTICED SMOKE AND FUMES COMING FROM TWO OF THE FORWARD CABIN SPEAKERS (LOUNGE AREA).  ONE SPEAKER EMITTED A FLAME APPROXIMATELY 2 TO 3 INCHES IN LENGTH.  THE TECHNICIAN QUICKLY SHUT DOWN ALL AIRCRAFT ELECTRICAL POWER, AND RETURNED TO THE DAMAGED SPEAKER AREA WITH AN ONBOARD FIRE EXTINGUISHER.  THE FLAME HAD SELF EXTINGUISHED, HOWEVER, THE CABIN WAS VERY SMOKEY AT THAT POINT.  UPON FURTHER EXAMINATION, (2) SPEAKERS HAD2L72 4F4  FRTA16WE   E2GL                 
20060922000862006092200086WP  2006       9          22         2006FA0000923    220060823G726130745732        CARBON SEAL                             AMD   FALC50FALCON900   2700160EU  GARRTTTFE731TFE7315BR        WP                              ENGINE          DETERIORATED    D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL13922JW                       038                                     (NR 4 CARBON SEAL, PN30745732, SN 010515810208),  (NR 5 CARBON SEAL, PN 30745742, SN 0119368002352) PILOTS REPORT HIGH OIL PRESSURE.  OIL PRESSURE FOLLOWED THROTTLE HIGH GEARBOX PRESSURE CAUSED BY DETERIORATION OF NR 4 AND NR 5 CARBON SEALS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L73 4F4  FRTA46EU   E6WE                 
20060926002412006092600241WP  2006       9          26         2006FA0000924    220060823G726130745742        CARBON SEAL                             AMD   FALC50FALCON900   2700160EU  GARRTTTFE731TFE7315BR        WP                              NR 5            DETERIORATED    D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL13922JW                       038                                     (NR 4 CARBON SEAL, PN30745732, SN 010515810208) (NR 5 CARBON SEAL, PN30745742, SN 011936802352)  PILOTS REPORT HIGH OIL PRESSURE.  OIL PRESSURE FOLLOWED THROTTLE HIGH GEARBOX PRESSURE CAUSED BY DETERIORATION OF NR 4 AND NR 5 CARBON SEALS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L73 4F4  FRTA46EU   E6WE                 
20060921001992006092100199CE  2006       9          21         2006FA0000925    120060917G5711082260039       SPAR CAP                                CESSNA310   310Q        2074242CE  CONT  O470  IO470*      17026SO                              WING            CORRODED        D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO07697045433                   310Q0930                                DURING THE ANNUAL INSPECTION, FOUND UPPER AND LOWER REAR SPAR DAMAGE ON THIS AIRCRAFT. THIS DAMAGE IS DUE TO CORROSION ON THE UPPER AND LOWER REAR SPAR CAPS.  THE UPPER REAR SPAR CAP DAMAGE IS LOCATED ON THE FORWARD SIDE OF THE REAR SPAR CAP EXTENDING IB FROM UNDER RIB PN 0822175-69 AT STATION 57.50. THIS DAMAGE IS APPROX. 3 INCHES HORIZONTALLY, .7500 INCH VERTICALLY AND .2500 IN DEPTH.  THE LOWER REAR SPAR CAP DAMAGE IS LOCATED ON THE FORWARD SIDE OF THE REAR SPAR CAP EXTENDING OB FROM UNDER RIB PN 0822175-69 AT STATION 57.50. THIS DAMAGE IS APPROX. 6 INCHES HORIZONTALLY AND THE ENTIRE LOWER SPAR CAP IN THIS AREA IS ESSENTIALLY MISSING.  THE LT WING HAS BEEN REMOVED AND SENT FOR REPAIR.                        1L72 3O3  O  3A10    E1CE                 
20060922000472006092200047CE  2006       9          22         2006FA0000926    120060919G7830HS78320009      THRUST REVERSER                         RAYTHNDH125 HAWKER800XP 7150012CE                                                                               CORRODED        B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09852QS5855                   258452                                  MAJOR CORROSION ON THE THRUST REVERSER DOOR RAMP SKINS DUE TO THE PAINT MISSING FROM THE RIVET HEADS.  BY MAJOR CORROSION, WE ARE BLENDING THE AREAS BELOW LIMITS AND HAVING TO SEND THEM OUT FOR REPAIR.  AREAS OF CORROSION ARE NOT ONLY BEING FOUND ON THE RIVET HEADS WE ARE FINDING SURFACE CORROSION ANYWHERE THE PAINT IS MISSING ON THE RAMP SKINS.                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F    RTA3EU                         
20060922000482006092200048CE  2006       9          22         2006FA0000927    120060919G7830                SKIN                                    RAYTHNDH125 HAWKER800XP 7150012CE                                                               THRUST REVERSER CORRODED        B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE09852QS5855       TECAV0114   258452                                  MAJOR CORROSION ON THE THRUST REVERSER DOOR RAMP SKINS DUE TO THE PAINT MISSING FROM THE RIVET HEADS.  BY MAJOR CORROSION I MEAN WE ARE BLENDING THE AREAS BELOW LIMITS AND HAVING TO SEND THEM OUT FOR REPAIR.  AREAS OF CORROSION ARE NOT ONLY BEING FOUND ON THE RIVET HEADS WE ARE FINDING SURFACE CORROSION ANYWHERE THE PAINT IS MISSING ON THE RAMP SKINS.                                                                                                                                                                                                                                                                                                                                                                               2L72 4F    RTA3EU                         
20060925001622006092500162NE  2006       9          25         2006FA0000928    220060919G7200                ENGINE                                  AGUSTAA109  A109E       0260119EU  TMECA ARRIUSARRIUS2K1        NE                                              MAKING METAL    C      O   OTHER                                                                                           J  WARNING INDICATION                                                            NRNOT REPORTED   1                      NM0891LF                        11509       33022                       ENGINE CHIP LIGHT CAME ON APPROACH TO LANDING. REMOVED GAS GENERATOR MAG PLUG FOUND COVERED WITH METAL CHIPS. PROBABLE CAUSE BEARING FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1G72 3U3  URTH7EU    E34NE                
20060926000302006092600030NE  2006       9          26         2006FA0000929    220060919G7200                ENGINE                                  AGUSTAA109  A109E       0260119EU  TMECA ARRIUSARRIUS2K1        NE                                              MAKING METAL    C      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM0891LF                        11509       33022                       ENGINE CHIP LIGHT CAME ON APPROACH TO LANDING. REMOVED GAS GENERATOR MAG PLUG FOUND COVERED WITH METAL CHIPS. PROBABLE CAUSE BEARING FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1G72 3U3  URTH7EU    E34NE                
20060921001872006092100187CE  2006       9          21         2006FA0000930    120060920G551145A21146006     RIB                                     BEECH MU300 400A        1155402CE  PWA   JT15  JT15D5      52112NE                              HORIZONTAL STAB CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO13939GP                       RK125       PCEJA0017                   THE HORIZONTAL STABILIZER RIB (RT SIDE) LOCATED UNDER THE ROLLER BRACKET HAD A CRACK IN IT. THIS ITEM IS COVERED UNDER COMMUNIQU NR 70.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2H72 4F4  FRTA16SW   E25EA                
20060921002122006092100212    2006       9          21         2006FA0000931    120060920G551145A211460506    RIB                                                                        PWA   JT15  JT15D5      52112NE                              HORIZONTAL STAB CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO1327XP                                                                THE RIBS LOCATED UNDER THE HORIZONTAL STABILIZER BRACKETS WERE CRACKED, BOTH THE LT AND RT SIDES. THIS IS COVERED UNDER COMMUNIQU NUMBER 70.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          4  F          E25EA                
20060921002132006092100213CE  2006       9          21         2006FA0000932    120060920G551145A211460506    RIB                                     BEECH MU300 400A        1155402CE  PWA   JT15  JT15D5      52112NE                              HORIZONTAL STAB CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO1327XP                        RK266                                   THE RIBS LOCATED UNDER THE HORIZONTAL STABILIZER BRACKETS WERE CRACKED, BOTH THE LT AND RT SIDES. THIS IS COVERED UNDER COMMUNIQUE NUMBER 70.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2H72 4F4  FRTA16SW   E25EA                
20060921002482006092100248EU  2006       9          21         2006FA0000933    120060806G32228904200484      AXLE                                    SOCATAMS894 MS894A      8402842EU  FRNKLN6AV3506V350*      27043EA  MCAULY2A31C 2A31C21     GL  NLG             BROKEN          G      O   OTHER                                                                                           O  OTHER                                                                         LDLANDING        1                      EA1733BF                        11720                                   INFORMATION OBTAINED FROM OWNER AND OPERATOR ENCOUNTERED AN INCIDENT UPON LANDING. AT TOUCHDOWN PILOT REPORTED THE NOSE LANDING GEAR AXLE BROKE, LIBERATING THE NOSE WHEEL FROM THE AIRCRAFT. THE NOSE WHEEL CONTACTED THE RT MAIN FLAP ASSY (DAMAGE SEVERITY UNKNOWN, REPLACEMENT APPARENTLY REQUIRED) SUBSEQUENTLY THE PROPELLER CONTACTED THE RUNWAY. PILOT REPORTED THE ENGINE DID NOT SUFFER SUDDEN STOPPAGE AND  THERE  WAS NO REPORTED INJURY OR DAMAGE TO AIRPORT PERSONNEL, EQUIPMENT OR PROPERTY.                                                                                                                                                                                                                                     1L71 3O3  O  7A14    E9EA    5  CP919     
20060921003192006092100319EA  2006       9          21         2006FA0000934    220060920G8500                ENGINE                                  CESSNA150   152         2071835CE  LYC   O235  O235L2C     41505EA                                              LACK OF LUBE    D      O   OTHER                                                                                           YJ ENGINE STOPPAGE           WARNING INDICATION                                  CRCRUISE         1                      SO055330B     2252              83838       L1395415                    LOSS OF OIL PRESSURE WHICH LED TO ENGINE FAILURE/SEIZE AND FORCED EMERGENCY LANDING ON HIGHWAY.  NO VISUAL PROBLEMS ON EXTERNAL AREA OF ENGINE.  REMOVED ENGINE AND SENT TO MFG FOR TEARDOWN AND EVALUATION.  MFG REPORTED  THAT ENGINE SUFFERED OIL STARVATION.  NR 1 AND NR 3 ROD JOURNALS WERE SCORED AND HEAT CHECKED BEYOND REPAIR.  SIGNATURE'S ESTIMATION OF OIL STARVATION WAS CAUSED BY DETONATION IN NR 1 CYLINDER.  THE NR 1 CYLINDER DETONATION, BURNED HOLE IN THE PISTON, CAUSING OIL TO BE BLOWN OUT OF ENGINE VENT TUBE.  THE NR 1 CAMSHAFT INTAKE LOBE WAS SEVERELY WORN AND THE EXHAUST LOBE MODERATELY WORN IN WHICH IS BELIEVED TO HAVE CONTRIBUTED TO THE NR 1 CYLINDER DETONATION PROBLEM.                                1H71 3O3  ONT3A19    E223                 
20060926001332006092600133CE  2006       9          26         2006FA0000939    120060913G3710S2501           HOSE                                    CESSNA172   172P        2072436CE  CONT  O470  IO470*      17026SO                              VACUUM SYS      FAILED          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL1398264                       17276271                                INVESTIGATION INTO FAILED ATTITUDE INDICATOR ON LISTED AIRCRAFT FOUND APPARENT CAUSE OF FAILURE TO BE FROM CONTAMINATION FROM DISINTEGRATING VACUUM HOSE.  THE HOSES IN QUESTION ARE MARKED B906 AND B904 HOSE.  TO PREVENT RECURRENCE, SB SEB96-10 SHOULD BE ACCOMPLISHED ON AIRCRAFT.  ON OTHER AIRCRAFT HOSE SHOULD BE REPLACED WITH APPROVED EQUIVALENT.  DUE TO SEVERITY OF POTENTIAL FOR HOSE TO CONTAMINATE, DAMAGE AND RENDER USELESS NEEDED EQUIPMENT IN IFR FLIGHT, SPECIAL CONSIDERATION SHOULD BE TAKEN TO REMOVE THIS PRODUCT FROM AIRCRAFT IT MIGHT HAVE BEEN INSTALLED AS SOON AS POSSIBLE.(K)                                                                                                                                   1H71 3O3  ONT3A12    E1CE                 
20060927000042006092700004CE  2006       9          27         2006FA0000940    120060823G2750                FLAP SYSTEM                             RAYTHN390   390         7150030CE                                                                               MISRIGGED       B  MGORO   OTHER                                                                                           W  INADEQUATE Q C                                                                NRNOT REPORTED   1                      CE099LV                         RB132                                   DURING PHASE INSPECTION FOUND THE LT IB AFT FLAP TRACK ATTACH BOLT CHAFED 3 LAYERS OF CARBON FIBER INTO THE FUSELAGE.  FOUND FLAP MISRIGGED AND TOP 3 FLAP TRACK FASTENERS WORKING.  RECOMMEND ADDITIONAL ATTENTION TO FLAP RIGGING AND ALL ATTACHING HARDWARE DURING PHASE INSPECTIONS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                   17 2 3F    RTA00010WI                     
20060927000082006092700008CE  2006       9          27         2006FA0000941    120060906G575339005214110002  FLAP TRACK                              RAYTHN390   390         7150030CE                                                               RT WING         DAMAGED         B  MGORO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE09701KB600                    RB103                                   DURING 200/600 HR PHASE INSPECTION FOUND THE RT IB AFT FLAP TRACK UPPER 3 ATTACH FASTENERS PN: MS90354S0609 WORKING.  RECOMMEND ADDITIONAL ATTENTION TO FLAP RIGGING AND ALL ATTACHING HARDWARE DURING PHASE INSPECTIONS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  17 2 3F    RTA00010WI                     
20060927000092006092700009CE  2006       9          27         2006FA0000942    120060906G575339005214110002  FLAP TRACK                              RAYTHN390   390         7150030CE                                                               RT WING         DAMAGED         B  MGORO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE09701KB600                    RB103                                   DURING 200/600 HR PHASE INSPECTION FOUND THE RT IB AFT FLAP TRACK UPPER 3 ATTACH FASTENERS PN: MS90354S0609 WORKING.  RECOMMEND ADDITIONAL ATTENTION TO FLAP RIGGING AND ALL ATTACHING HARDWARE DURING PHASE INSPECTION.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   17 2 3F    RTA00010WI                     
20060927000072006092700007CE  2006       9          27         2006FA0000944    120060911G81204709440029      RELIEF VALVE                            CESSNA182   T182T       2072738CE  LYC   O540  TIO540AK1A       EA                              WASTEGATE       FAILED          B  Z08RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE07182GA89         ILN00185    T18208587   L1240661A                   PILOT REPORTED, ON TAKEOFF ROLL, THE MANIFOLD PRESSURE WENT TO GREATER THAN 40 MP FOR 3 TO 4 SECONDS.  THE PILOT WENT BACK TO RUNUP AREA AND CONFIRMED THAT MP COULD GO ABOUT 40 MP, PILOT TAXIED BACK TO RAMP AND GROUNDED AIRCRAFT.  TROUBLESHOT TURBO CHARGER SYSTEM FOUND THE TURBO CHARGER WASTEGATE CONTROLLER HAD FAILED.  REMOVED WASTEGATE CONTROLLER AND PRESSURE RELIEF VALVE AND SENT FOR CHECKOUT.  FOUND THE WASTE CONTROLLER BAD AND THE PRESSURE RELIEF VALVE WAS FACTORY PRESENT TO THE INCORRECT MP PRESSURE WHICH IF SET CORRECTLY COULD HAVE PREVENTED THE ENGINE FROM OVERBOOSTING.  THIS AC ENGINE TURBOCHARGING SYS HAD A DUEL SYS FAILURE.  SB 369J ADDRESSES WHAT SHOULD BE DONE WHEN ENG IS OVERBOOSTED.  MFG RECOMMEN1H71 3O3  ONT3A13                         
20060927000122006092700012CE  2006       9          27         2006FA0000945    120060707G7120                MOUNT                                   BEECH 76    76          1153005CE  LYC   O360  O360*       41514EA                              RT ENGINE       BROKEN          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW992009X                       ME66                                    BOTH LT AND RT ENGINE MOUNT TO FIREWALL ATTACH POINTS BROKE OUT AFT OF THE FIREWALL IN THE UPPER OB POINT.  THIS BREAKAGE IS DIFFICULT TO DETECT DUE TO VISIBILITY ACCESS.  THESE BRACKETS BROKE BECAUSE OF FLIGHT THROUGH TURBULENCE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L72 3O3  O  A29CE   E286                 
20060927000022006092700002CE  2006       9          27         2006FA0000946    120060707G712010598000021     ATTACH ANGLE                            BEECH 76    76          1153005CE  LYC   O360  O360*       41514EA                              ENGINE MOUNT    BROKEN          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW992009X                       ME66                                    BOTH LT AND RT ENGINE MOUNTS TO FIREWALL ATTACH POINTS BROKE OUT AFT OF THE FIREWALL IN THE UPPER OB POINT.  THIS BREAKAGE IS DIFFICULT TO DETECT DUE TO VISIBILITY ACCESS.  THESE BRACKETS BROKE BECAUSE OF FLIGHT THROUGH TURBULENCE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L72 3O3  O  A29CE   E286                 
20060927000382006092700038GL  2006       9          27         2006FA0000947    220060908G72406870992         COMBUSTION CASE                         HUGHES369   369D        4470706WP  ALLSN 250C  250C20B     03013GL                              ENGINE          CRACKED         B  EOORO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      AL0390431                       1100833D    CAE830468                   PILOT COMPLAINED THAT THE TOT SUDDENLY WENT 40 DEGREES C, HOT.  FOUND OUTER COMBUSTION CAN CRACKS.  REPLACED UNIT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1G71 3U3  U  H3WE    E4CE                 
20060926000602006092600060GL  2006       9          26         2006FA0000948    220060908G720023057142        CASE                                    HUGHES369   369D        4470706WP  ALLSN 250C  250C20B     03013GL                              ENGINE          ERODED          B  EOORO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      AL03CFASX     684               1150D       CAE830467                   FOUND CASE HALVES SHOT.  ENGINE RUNNING 35 DEGREES C, HOT. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1G71 3U3  U  H3WE    E4CE                 
20060926000102006092600010EA  2006       9          26         2006FA0000949    120060907G56106003303025      WINDSHIELD                              CNDAIRCL600 CL6002A12   1900304EA                                                               COCKPIT         CRACKED         B  SH5RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA63150MH                       3021                                    LT WINDSHIELD (PILOTS) OUTER-PLY CRACKED DURING FLIGHT.  NO KNOWN CAUSE AS TO THE EVENTS LEADING TO CRACK.  KNOWN TO BE A COMMON FAILURE ON CHALLENGER  ACRYLIC WINDSHIELD AND SIDE WINDOWS.  WHETHER DUE TO IMPACT OF SOME SORTS OR WINDSHIELD NEAT FAILURE OR DELAMINATION.   WINDSHIELD AND AC WAS RTSD AS AIRWORTHY.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F    RTA21EA                        
20060926002562006092600256EA  2006       9          26         2006FA0000950    120060907G56106003303025      WINDSHIELD                              CNDAIRCL600 CL6002B16   1900305EA  GE    CF34  CF34*            NE                              COCKPIT         CRACKED         B  SH5RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA63500PE                       5440                                    LT WINDSHIELD (PILOTS) OUTER-PLY CRACKED DURING FLIGHT.  NO KNOWN CAUSE AS TO THE EVENTS OF THE CRACK.  KNOWN TO BE A COMMON FAILURE ON CHALLENGER ACRYLIC WINDSHIELD AND SIDE WINDOWS.  WHETHER DUE TO IMPACT OF SOME SORTS OR WINDSHIELD HEAT FAILURE OR DELAMINATION.  WINDSHIELD WAS REMOVED AND REPLACED WITH A NEW WINDSHIELD AND AC WAS RETURNED AS AIRWORTHY.  (K)                                                                                                                                                                                                                                                                                                                                                                      2L72 4F4  FRTA21EA   E15NE                
20060926002482006092600248NE  2006       9          26         2006FA0000951    120060908G32136525108027103   AXLE                                    SKRSKYS64   CH54B       8142610NE  PWA   JFTD12JFTD12A5A   52047NE                              MLG             CRACKED         B  JYDRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM09158AC                       64081                                   (REF NR: MDR06-091) UPON DISASSEMBLY, AXLE WAS FOUND TO BE CRACKED AND RUNS AROUND THE CIRCUMFERENCE.  THE TRACTURE APPEARS TO ROIGINATE IN THE WELD ON THE CENTER OF THE AXLE SHAFT.  THE AXLE WAS FRACTURED UNDER THE SOCKET, PN 6425-50202-101, AS EVIDENCED BY A CRACK EXTENDING AROUND THE CIRCUMFERENCE OF THE SOCKET, FROM APPROXIMATELY THE 10:00 TO 2:00 POSITION.  NO RECENT EVENTS ARE KNOWN THAT MAY HAVE CONTRIBUTED TO THIS TYPE OF FAILURE.  RECOMMENDATIONS TO PREVENT RECURRENCE:  A ONE PIECE AXLE IS AVAILABLE FOR USE IN LIEU OF THE 2 PIECE WELDED AXLE.  (K)                                                                                                                                                              2G72 4U4  U  H6EA    E15EA                
20060926001322006092600132CE  2006       9          26         2006FA0000952    120060908G3240                LINE                                    BEECH MU300 400A        1155402CE  PWA   JT15  JT15D5      52112NE                              BRAKE           CHAFED          B  E81RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL03785TA                       RK239                                   DURING A SCHEDULED INSPECTION FOUND PN 128580101-1, BRAKE LINE ASSY CHAFE DAMAGED BY EXCESS LENGTH CABIN FLOOR PANEL ATTACH SCREW AS DESCRIBED IN MFG SB 53-3511.  REPAIR REQUIRED SPLICING IN OF NEW BRAKE LINE SEGMENT IAW SB 53-3511.  HAVE FOUND THIS CONDITION ON NUMEROUS OTHER AC.  RECOMMEND THAT SB 53-3511 BE CHANGED TO A MANDATORY SB DUE TO COMMON OCCURRENCE AND POSSIBILITY FOR LOSS OF BRAKING ACTION IF TUBING CHAFED THROUGH.  ALSO RECOMMEND AN ALERT INFO BULLENTIN ON THIS SUBJECT.(K)                                                                                                                                                                                                                                     2H72 4F4  FRTA16SW   E25EA                
20060927000012006092700001    2006       9          27         2006FA0000954    420060907G34601017241011      CDU                                     AMD   FALC50FALCON50MYST2730106EU  GARRTTTFE731TFE731*     01518WP                              COCKPIT         BURNED          B  JGVRO   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      NRNOT REPORTED   1                      CE0948KR                        127                                     SMOKE EMANATING FROM NR 1 FMS CDU DURING CRUISE FLIGHT.  UNIT SMELLED OF SMOKE AND WOULD NOT POWER UP DURING INITIAL BENCH CHECK.  FURTHER TEARDOWN PENDING.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L73 4F4  F  A46EU   E6WE                 
20060926001252006092600125SO  2006       9          26         2006FA0000955    220060925G8530AEC631397CN2C   CYLINDER                                BEECH 36    A36         1151604CE  CONT  O550  IO550B           SO                              EXHAUST PORT    CRACKED         B      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO094307S133                    E675        281757                      NOTED ON 6 ENGINE COMPONENTS, INC. ECI CYLINDERS WITH 133.1 SINCE NEW AND PUT IN SERVICE ON THE SAME ENGINE DECEMBER 2004.  NR4 AND NR5 CYLINDERS WERE CRACKED IN THE EXHAUST PORT WITH A HOLE BURNED THROUGH AT THE CRACK AND WAS LEAKING EXHAUST GASSES OVERBOARD. NR 1, NR 2, NR 3 AND NR 6 CYLINDERS WERE CRACKED IN THE SAME LOCATION AS NR 4 AND NR 5. THE CRACKS ARE IB OF THE EXHAUST GUIDE BOSS. THE THICKNESS OF THE MATERIAL IN THAT AREA OF THE EXHAUST PORT APPEARS TO BE TOO THIN AND NOT ABLE TO WITHSTAND THE HEAT AND STRESS PRESENT DURING NORMAL ENGINE OPERATION.                                                                                                                                                           1L71 3O3  O  3A15    E3SO                 
20060926002472006092600247GL  2006       9          26         2006FA0000957    220060919G72306876873         IMPELLER                                HUGHES369   369D        4470706WP  ALLSN 250C  250C20B     03013GL                              COMPRESSOR      DAMAGED         B  EOORK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03511SB289                    1090592D    CAE834272                   DURING REPLACEMENT OF THE S16 SHAFT, IT WAS DISCOVERED THAT THE OUTER LAND OF THE SNAP RING GROOVE WAS VERY THIN AND THE INNER EDGE WAS LIFTING AND (2) .3750 INCH LONG PIECES CAME OFF OF THE LAND.  WHEN THE SNAP RING WAS REMOVED THE GROVE FOR THE  SNAP RING SEEMS TO BE THE NORMAL DIMENSION.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                        1G71 3U3  U  H3WE    E4CE                 
20060927000032006092700003GL  2006       9          27         2006FA0000958    220060919G725023038241        TURBINE WHEEL                           HUGHES369   369D        4470706WP  ALLSN 250C  250C20B     03013GL                              ENGINE          DAMAGED         B  EOORO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      AL03511SB12352208               1090592D    CAE834272                   FOUND NR 1, AND NR 2 TURBINES RUBING AFTER ENGINE DISASSEMBLY FOR CHIPS.  DURING 100 HR CHIPS WERE FOUND ON THE CHIP PLUGS.  DISASSEMBLED ENGINE AND DISCOVERED THE N1 AND N2 TURBINES WERE RUBBING, REPLACED UNIT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1G71 3U3  U  H3WE    E4CE                 
20060926002432006092600243GL  2006       9          26         2006FA0000959    220060919G72106894171         GEARBOX                                 HUGHES369   369D        4470706WP  ALLSN 250C  250C20B     03013GL                              ENGINE          MAKING METAL    B  EOORO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      AL03511SB126174455              1090592D    CAE834272                   FOUND PTO , PTO BALL BEARING AND TORQUEMETER SPALLED.  FOUND CHIPS ON CHIP PLUGS.  DISASSEMBLED GEAR BOX AND FOUND PTO GEAR, TORQUEMETER GEAR AND PTO BALL BEARING SPALLED.  REPLACED GEARBOX.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1G71 3U3  U  H3WE    E4CE                 
20061018000832006101800083SO  2006       10         18         2006FA0000961    220060919G8520656935          CRANKCASE                                                                  CONT  O520  GTSIO520*   17032SO                              ENGINE          LEAKING         B  VA1RK   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      SW19                                        292082                      POROSITY IN CRANKCASE NOSE SECTION ON THE RT SIDE BY THE OIL GALLEY PLUG.  LEAKS OIL, MFG HAS BEEN NOTIFIED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      3  O          E7CE                 
20061019001632006101900163SO  2006       10         19         2006FA0000962    220060919G8550656935          CRANKCASE                                                                  CONT  O520  GTSIO520*   17032SO                              ENGINE          LEAKING         B  VA1RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW19                                        604918                      POROSITY IN CRANKCASE NOSE SECTION ON THE RT SIDE BY THE OIL GALLEY PLUG.  LEAKS OIL.  MFG HAS BEEN NOTIFIED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     3  O          E7CE                 
20061018000462006101800046    2006       10         18         2006FA0000963    120060918G493038828406        FCU             HONEYWELL                                                                                                               APU FUEL        CORRODED        B  QKPRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO05                                                                    FUEL PRESSURE IN THE DIFFERENTIAL PRESSURE VALVE IS CAUSING SEVERE PITTING INSIDE THE FCU HOUSING.  THIS PITTING INSIDE THE FCU HOUSING.  THIS PITTING EVENTUALLY BECOMES A PIN HOLE IN THE HOUSING.  THIS PIN HOLE ALLOWS A STREAM OF FUEL TO EXIT THE FCU DURING OPERATION.  IF THE PROBLEM IS NOT CORRECTED IT COULD CREATE A POTENTIAL FIRE HAZZARD.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                             
20061011001472006101100147CE  2006       10         11         2006FA0000964    120060919G5340AN743A          ATTACH BOLT                             BEECH 23    C23         1151242CE  LYC   O360  O360A4K     41514EA  SNSNCH76E   76EM8       EA  ALTERNATOR      WORN            D  PVQGO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL159239S                       M1732       L2046036A   17458K          DURING PRE-RUNUP INSPECTION FOR ANNUAL INSPECTION ALTERNATOR BELT NOTED TO BE LOOSE.  UPON INSPECTION OF ALTERNATOR FOR BELT TENSION THE FOLLOWING WAS NOTED:  THE CASTLE NUT WAS BACKED OUT TO THE POINT OF CHAFING ON THE A+ WIRE, THE WIRE WAS KEEPING THE NUT FROM BACKING ALL OF THE WAY OFF OF THIS ATTACHMENT BOLT.  THIS AIRCRAFT AND ENGINE COMBINATION HAD BEEN INSPECTED FOR ANNUAL AIRWORTHINESS BY THE SAME INSPECTION 3 TIMES DURING THE PAST 22.1 HRS.  NOTE ENCLOSED PHOTOS.  THIS ENGINE HAS 237 HRS SINCE MAJOR OVERHAUL BY AN APPROVED SHOP AND WOULD ESTIMATE THAT THE NUT HAD NOT BEEN SAFTIED DURING ANY OF THIS TIME AS THE NUT WOULD ACTUALLY SLIDE ACROSS THE THREADS OF THE BOLT.  (K)                               1L71 3O3  O  A1CE    E286    5  NP4EA     
20061011001832006101100183SO  2006       10         11         2006FA0000965    120060902G3230211C23412       PRESSURE SWITCH                         PIPER PA32  PA32R301T   7103220SO  LYC   O540  TIO540AH1A  42003EA                              MLG PUMP        FAILED          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO0598LA                        3257031     L992361A                    AT AN ANNUAL INSPECTION IT WAS NOTED THE MAIN GEAR FAILED TO CYCLE COMPLETELY BEFORE PUMP SHUT OFF.  PUMP CYCLED ON AND OFF UNTIL MAINS WERE FULLY RETRACTED.  PUMP THEN REMAINED OFF.  PRESSURE SHUT OFF SWITCH WAS CHECKED WITH A HIGH PRESSURE GAUGE AND IT WAS FOUND TO TRIP AT 1400 LB WELL BELOW THE 1800 LG IT WAS DESIGNED FOR.  SWITCH IS ESTIMATED TO HAVE MADE 500 CYCLES BEFORE FAILING.  IT IS NOTED THAT THIS IS MY FIRST INSPECTION OF THIS AIRCRAFT SO THE PROBLEM MAY HAVE BEEN OVER LOOKED IN THE PAST.  (K)                                                                                                                                                                                                                  1L71 3O3  O  A3SO    E14EA                
20061012000732006101200073GL  2006       10         12         2006FA0000966    320060918G6114C6132C67        HUB                                     CESSNA172   T41D               CE  CONT  O360  IO360D      17025SO  MCAULY2A34C D2A34C67    GL  PROPELLER       CRACKED         B  LT4RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO19                                                    686342          PROPELLER RECEIVED FOR REPAIR, RED DYE OIL LEAK.  PROPELLER WAS DISASSEMBLED AND BLADE RETENSION THREADS EDDY CURRENT INSPECTED.  NR2 BLADE RETENTION THREAD, 4 THREADS IN AT APPROXIMATELY 7 O`CLOCK POSITION FOUND CRACKED.  HUB REMOVED FROM SERVICE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3O3  O  3A17    E1CE    5  CP3EA     
20061012001232006101200123CE  2006       10         12         2006FA0000967    120060922G5610121140019       WINDOW                                  CESSNA206   T206H       2073303CE  LYC   O540  TIO540*     41532EA                              REAR WINDOW     DAMAGED         B  H5GRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA07217DL674                    T20608224                               THE FACTORY ORIGINAL REAR WINDOW OF THIS AC BEGAN TO DEVELOP A CONCAVE AREA IN THE CENTER OF THE WINDOW.  THIS AREA WOULD BECOME MORE PRONOUNCED IN DIRECT SUNLIGHT.  THIS AC IS 6 YEARS OLD AD HAS ACCUMULATED 674.52 HOURS.  THE AC WAS HANGER KEPT MOST OF THE TIME.  THE WINDOW WAS REPLACED WITH A NEW UNIT MEASURING .250 INCH THICK.  AMPLE CLEARANCE WAS MAINTAINED TO PROVIDE ROOM FOR EXPANSION AND CONTRACTION YET STILL MAINTAINING ADEQUATE ENGAGEMENT OF WINDOW  INTO WINDOW RETAINER.  THE ORIGINAL WINDOW MEASURED .125 INCH THICK.  THIS INSTALLATION WAS PERFORMED UNDER THE FIELD APPROVAL PROCESS AND REQUIRED ONLY MINOR BENDING AND REFORMING OF THE RETAINER FLANGE OF THE AIRCRAFT STRUCTURE TO ACCEPT THIS NEW THICKER 1H71 3O3  ORTA4CE    E14EA                
20061012001212006101200121CE  2006       10         12         2006FA0000968    120060919G243523085001        STARTER GEN                             BEECH B300  B300        1159232CE  PWA   PT6   PT6A60A     52043NE  HARTZLHCB4M HCB4MP3     GL  LEFT            WORN            B  AHTRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL11200VC1737 712               FL316                                   IN FLIGHT THE LT SIDE STARTER/GEN AFT BEARING AT THE COOLING FAN FAILED AND THE GENERATOR FAILED.  THE AC RETURNED TO ITS DEPARTURE TERMINAL WITHOUT INCIDENT.  THE STARTER/GEN WAS REPLACED AND THE CHARGING AND ELECTRICAL SYSTEM OPS, CHECKED GOOD.  NO KNOWN CAUSE, STARTER/GEN WAS WITHIN THE 1000 HRS FOR BEING OVERHAULED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4T4  TRTA24CE   E4EA    6  CP56GL    
20061012001222006101200122SO  2006       10         12         2006FA0000969    120060927G2140A23D04          SHUTOFF VALVE   JANITROL                PIPER PA31  PA31        7103102SO  LYC   O540  TIO540*     41532EA                              HEATER          LEAKING         D      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      AL0316SC 750        1997221     31639                                   DURING ANNUAL INSPECTION FOUND FUEL LEAKING AROUND DIAPHRAGM JOINT.  PART MADE BY DURING FIRST QUARTER OF 2001.  PN A23D04, 7.5 PSI, 24 VOLT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L72 3O3  O  A20SO   E14EA                
20061018001342006101800134SO  2006       10         18         2006FA0000970    120061002G3210AN617           BOLT                                    PIPER PA31  PA31350     7103110SO                                                               MLG             BROKEN          G      O   OTHER                                                                                           O  OTHER                                                                         APAPPROACH       1                      SO054093W24842250               318152176                               MFG SL NR 1092, DATED 06/15/2005 DEALS WITH REPLACEMENT OF RETRACTION ARMS, P/N 42042-000 OR 42042-002 AT 6000 HOURS AND TO PERFORM INSPECTION FOR CRACKS USING 10X MAGNIFYING GLASS AND DYE PENETRANT AFTER REACHING 1500 HOURS AND AT EACH 250 HOURS THERE-AFTER UNTIL ACCUMULATION OF 6000 HOURS. THERE IS NO INSPECTION CRITERIA FOR INSPECTION AND REPLACEMENT OF ATTACHING HARDWARE. ATTACHMENT BOLTS HAVE BEEN VISUALLY INSPECTED EACH 250 HOURS WHEN REMOVED TO INSPECT RETRACTION ARMS. HOWEVER, BOLT FAILED AND WAS FOUND BROKEN AND SHEARED OFF WITH ONLY HEAD PORTION STILL IN PLACE. IT APPEARS THAT WITH BOLT SHEARED, THE LANDING GEAR ACTUATOR WAS PLACED IN A BIND WHICH BROKE THE BALL LINK THAT SCREWS IN THE MAIN SHAFT OF T1L72 3O      A20SO                        
20061121001112006112100111SO  2006       11         21         2006FA0000971    220060926G732055P70D5E608     VALVE                                   MOONEYM20   M20K        5870220SW  CONT  O360  TSIO360GB   17025SO                              ENGINE FUEL     LEAKING         D      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      NM09231GR1340                   250087      309083                      THE FUEL PRIMER DIVERTER VALVE P/N 642199 (P/N 55P70D5E-608) LEAKED FUEL OVER THE TOP OF THE ENGINE IN FLIGHT, IT WAS LEAKING SO MUCH THE ENGINE WOULD NOT KEEP RUNNING WITHOUT THE USE OF THE ELECTRIC BOOST PUMP. INITIALLY OUR MFG VENDOR GAVE ME A REPLACEMENT P/N 633862 AND SAID NO PARTS WERE AVAILABLE. SO I CONTACTED THE MFG ENGINEERING AND SPOKE WITH THEIR REPAIR STATION MANAGER. HE INFORMED ME THAT THEY HAD JUST OVERHAULED A VALVE THAT HAD CAUSED AN ENGINE FIRE, AND THEY OVERHAUL 8-10 A YEAR. HE ALSO SAID THE OVERHAULED VALVES HAVE PMA AND WILL NEVER LEAK AGAIN. I CALLED MFG AND PASSED ON THE PROBLEM TO THEIR TECH REP, HE DID INFORM ME THAT THEY DO IN FACT STOCK THE NEW P/N VALVE. I CANNOT FIND ANY BULLETINS 1L71 3O3  O  2A3     E9CE                 
20061019002002006101900200SO  2006       10         19         2006FA0000974    120060929G28231138303         SELECTOR VALVE                          PIPER PA18  PA18125     7101812SO  LYC   O290  O290*       41506EA                              FUEL SYSTEM     FAILED          D      A   UNSCHED LANDING                                                                                 YJ ENGINE STOPPAGE           WARNING INDICATION                                  CRCRUISE         1                      AL051896A     45                181728                                  FUEL SELECTOR/SHUTOFF VALVE HANDLE MOVED BUT VALVE DID NOT SELECT FROM LT FUEL TANK TO RT FUEL TANK. ENGINE RAN OUT OF FUEL FROM THIS AND AIRCRAFT LANDED ON ROAD. AD 60-10-08 WAS COMPLIED WITH 45 HOURS EARLIER. IA MECHANIC SUGGESTS THAT ROUTINE CLEANING OF VALVE AND INSPECTION OF PLASTIC PLUGS AROUND SHAFT MOUNTING HOLES CRACKS OR REPLACEMENT OF PLASTIC PLUGS WITH BRASS PLUGS. TIME IN SERVICE OF SELECTOR VALVE 11383-03 UNKNOWN.                                                                                                                                                                                                                                                                                                 1H71 3O3  O  1A2     E229                 
20061018000502006101800050EA  2006       10         18         2006FA0000975    220061003G74141052949         DISTRIBUTOR BLK CONT                    ROBSINR22   R22BETA     7640110NM  LYC   O320  O320B2C     41508EA                              MAGNETO         FAILED          G      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP238280J           4772011     0892        L1492539A                   DURING 500 H0UR INSPECTION AND SERVICE THE DISTRIBUTOR BLOCK BRONZE BUSHING WAS FOUND TO BE BROKEN AND FREE TO MOVE AROUND.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1G71 3O3  O  H10WE   E274                 
20061012001202006101200120    2006       10         12         2006FA0000976    220061003G853015070001        EXHAUST HEADER                          CIRRUSSR    SR22        2130001GL                                                               ENGINE          CRACKED         G      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP23253SR50                     2034                                    NR 5 EXHAUST STACH/HEADER WAS FOUND TO BE CRACKED AT THE CYLINDER FLANGE AT THE WELD.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L71 3O    NTA00009CH                     
20061018000322006101800032EU  2006       10         18         2006FA0000977    120061003G3260803682          PROXIMITY SENSOR                        AMD   FALC50FALCON50MYST2730106EU                                                               MLG             FAILED          B      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            LDLANDING        1                      SW11784B                        118                                     GEAR SELECTED (DOWN), LT GEAR DOOR INDICATION LIGHT REMAIND RED. MANUAL GEAR PROCEDURES USED TO CLOSE DOOR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L73 4F      A46EU                        
20061018000412006101800041SO  2006       10         18         2006FA0000979    220060915G853015070001        EXHAUST HEADER                          CIRRUSSR    SR22        2130001GL  CONT  O550  IO550N      17042SO                              NR 5            CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL15253SR50                     2034                                    NR 5 EXHAUST HEADER CRACKED AT CYLINDER FLANGE AT THE WELD.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L71 3O3  ONTA00009CHE3SO                 
20061018000422006101800042SO  2006       10         18         2006FA0000980    220060929G7414M3548           ROTOR           SLICK                   PIPER PA18  PA18        7101802SO  CONT  C90   C90*        17009SO                              RT MAGNETO      INOPERATIVE     D      A   UNSCHED LANDING                                                                                 R  PARTIAL RPM/PWR LOSS                                                          CLCLIMB          1                      AL037472D400        94010288    185807                                  PILOT NOTICED LACK OF POWER AND ROUGHNESS AFTER TAKEOFF.  RETURNED TO FIELD, DISCOVERED INOPERATIVE RT MAGNETO.  DISASSEMBLY OF RT MAGNETO REVEALED ROTOR SHAFT HAD SHEARED FLUSH WITH BOTTOM OF CAM CUTOUT.  THE REMAINING ROTOR AND DISTRIBUTOR BOTH ROTATED FREELY.  NO EVIDENCE OF PROBLEMS WITH EITHER GEAR.  PROBABLE CAUSE IS A DEFECT IN MFG (POSSIBLY BAD METAL OR STRESS CRACK FROM MACHINING CAM SLOT.  (K)                                                                                                                                                                                                                                                                                                                          1H71 3O3  O  1A2     E252                 
20061018000402006101800040NM  2006       10         18         2006FA0000981    120061006G282007166171        FUEL LINE                               UNIVAR108   108         9230402NM                                                               LT DOOR POST    CHAFED          D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM04933D 5401                   1082933                                 AILERON CABLE HAD CHAFED 90 PERCENT THRU FUEL LINE. AREA A LITTLE HARD TO SEE. FOUND BY LOOKING FOR NAV LIGHT SQUAWK THAT LED TO THE LT UPPER DOOR POST AREA. SUGGEST THAT ALL SIMILAR STYLE MFG WITH AILERON CABLE THAT RUNS ALONG FUEL LINES TO BE INSPECTED AND INSTALL SOME FORM OF ANTI-CHAFING MATERIAL TO THE AFFECTED AREA.                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3O      A767                         
20061019001752006101900175CE  2006       10         19         2006FA0000983    120061009G7603                CONTROL CABLE                           CESSNA172   172RG       2072438CE  LYC   O360  O360F1A6    41514EA                              CARBUETOR       FAILED          D      K   NONE                                                                                            O  OTHER                                                                         TXTAXI/GRND HDL  1                      CE079991B84                     172RG1110   L297946A                    UPON SHUTDOWN AFTER FLIGHT, PILOT PULLED ON CARBURETOR MIXTURE CABLE TO IDLE CUT-OFF. THE CABLE CAME OUT IN THE PILOTS HAND. SUSPECT CARBURETOR MIXTURE CABLE BROKE DURING FLIGHT. SUSPECT CABLE HAS A QUALITY ISSUE. NOTE: DID NOT EFFECT OPERATION OF AIRCRAFT DURING FLIGHT. REPLACED CABLE WITH NEW.                                                                                                                                                                                                                                                                                                                                                                                                                                        1H71 3O3  O  3A17    E286                 
20061026001722006102600172GL  2006       10         26         2006FA0000984    320060918G6114C6132C67        HUB             MCAULY                  CESSNA172   T41D               CE  CONT  O360  IO360D      17025SO  MCAULY2A34C D2A34C67    GL  PROPELLER       CRACKED         B  LT4RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO19     3250 1101  686342                              806058          PROPELLER RECEIVED FOR 60 MONTH OVERHAUL.  PROPELLER WAS DISASSEMBLED AND BLADE RETENTION THREADS EDDY CURRENT INSPECTED.  NR1 BLADE RETENTION THREAD, 4 THREADS IN AT APPROX 7 TO 8 OCLOCK POSITION FOUND CRACKED.  HUB REMOVED FROM SERVICE. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O3  O  3A17    E1CE    5  CP3EA     
20061025001272006102500127SO  2006       10         25         2006FA0000985    220060922G7310156F0034S0244   LINE                                    CESSNA421   421C        2076016CE  CONT  O520  GTSIO520N   17032SO                              ENGINE FUEL     RUPTURED        B  SI6RO   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  NRNOT REPORTED   1                      SW17469S 1120                   421C1057    808347R                     FUEL HOSE RUPTURED, SPRAYING FUEL ON THE HOT EXHAUST MANIFOLD TO TURBO CHARGER CAUSING AN ENGINE FIRE ON THE GROUND.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 3O3  O  A7CE    E7CE                 
20061025001282006102500128SO  2006       10         25         2006FA0000986    120060825G3210ANG17           BOLT                                    PIPER PA31  PA31350     7103110SO  LYC   O540  TIO540*     41532EA                              MLG             BROKEN          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO054093W24842                  318152176                               AIRCRAFT HAD GEAR UNSAFE LIGHT AND NO LT DOWN AND LOCKED INDICATION LIGHT, AS WELL.  THE GEAR HANDLE WOULD NOT RETURN TO NEUTRAL POSITION.  AIRCRAFT LANDED WITHOUT INCIDENT.  WE BELIEVE THAT THE UPPER BOLT THAT RETAINS THE MAIN GEAR RETRACTION ARM BROKE DUE TO FATIGUE.  THIS ALLOWED THE MAIN GEAR ACTUATOR TO BIND ON THE UPPER SECTION OF THE DRAG LEG AND BROKE THE MAIN GEAR ACTUATOR BALL END OUT OF THE MAIN SHAFT OF THE ACTUATOR.  THERE IS SL NR 1092, DATED JUNE 15TH, 2005 THAT REQUIRES THE MAIN GEAR RETRACTION ARMS, PN 42042000 OR 42042002 TO BE INSPECTED USING A 10X MAGNIFYING GLASS AND LIQUID PENETRANT INSPECTION AFTER REACHING 1500 HOURS TIME IN SERVICE AND THERE AFTER AT EACH 250 HOURS UNTIL THAT PART REACH1L72 3O3  O  A20SO   E14EA                
20061016002692006101600269CE  2006       10         16         2006FA0000987    120060922G282025160281        LINE                                    LEAR  35    31          5170530CE  GARRTTTFE731TFE731*     01518WP                              BOOST PUMP      CHAFED          B  UO2RO   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      GL195VG                         014                                     BLEED AIR CLAMP POSITIONED OB OF FUEL LINE CHAFED INTO FUEL LINE CAUSING A FUEL LEAK WITH BOOST PUMP PRESSURE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F4  FRTA10CE   E6WE                 
20061016002182006101600218CE  2006       10         16         2006FA0000988    120060907G3240215286          BRAKE ASSY                              CESSNA501   551         2076605CE  PWA   JT15  JT15D4      52112NE                              LT MLG          BROKEN          D      D   RETURN TO BLOCK                                                                                 J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      GL03502CL     317               5510002                                 DURING TAXI ON RAMP, LT BRAKE LOCKED UP (AIRCRAFT WAS MOVING AT A VERY LOW RATE OF SPEED).  AFTER REMOVAL OF LT WHEEL, FOUND 1 STATOR BROKEN IN HALF, DROPPING DOWN ONTO WHEEL (BRAKE KEY), CAUSING WHEEL TO LOCK UP.  NO DAMAGE NOTED TO WHEEL OR ANY OTHER PART OF AIRCRAFT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L72 4F4  F  A27CE   E1NE                 
20061016002902006101600290CE  2006       10         16         2006FA0000989    120060922G55324555030001803   PANEL                                   LEAR  45    45LEAR      5170805CE  GARRTTTFE731TFE731*     01518WP                              VERTICAL STAB   CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NE0310J                         063                                     DURING MAINTENANCE, DISCOVERED PANEL HAD 6 INCHES LONG CRACK RUNNING VERTICAL AT FWD ATTACH HOLES.  PANEL WAS REPLACED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F4  FRTT00008WIE6WE                 
20061018001052006101800105SO  2006       10         18         2006FA0000990    120060914G242060A4111810R     BRUSH HOLDER                            PIPER PA28  PA28161     7102803SO  LYC   O320  O320*       41508EA                              ALTERNATOR      WORN            C      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NE0336116637                    287816614                               DURING AC OPERATION, ALTERNATION CEASED PUTTING OUT POWER.  UPON INSPECTION AFTER REMOVAL, FOUND FIELD BRUSHES PREMATURELY WORN, AND COCKED OVER IN BRUSH HOLDER.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L71 3O3  O  2A13    E274                 
20061020000332006102000033SO  2006       10         20         2006FA0000991    120060914G24204111810         ALTERNATOR                              PIPER PA28  PA28R201    7102816SO                                                               ENGINE          INOPERATIVE     D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NE032241Q109                    28R7737029                              ALTERNATOR CEASED OPERATION WITH ONLY 109 HOURS ON IT IN LIKE NEW CONDITION.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L71 3O      2A13                         
20061018000302006101800030WP  2006       10         18         2006FA0000992    220060907G7200                ENGINE                                  RAYTHNDH125 HAWKER800XP 7150012CE  GARRTTTFE731TFE7315BR        WP                              NR 2            FAILED          B  AN3RA   UNSCHED LANDING                                                                                 XTJENGINE FLAMEOUT           ENGINE CASE PENETRATION   WARNING INDICATION        CRCRUISE         1                      SO33800WW                       258661      P107869                     (REF NR:  2006-1001)  30,000 FT, ENGINE BANG, ENGINE WAS SHUTDOWN AND FLIGHT DIVERTED.  NR 2 ENGINE TURBINE WHEEL FAILURE, UNCONTAINED.  INITIAL VISUAL INSPECTION POSSIBLE TURBINE WHEEL FAILURE.  INVESTIGATION IN PROCESS WITH ASSISTANCE FROM MFG.  PORTION OF ENGINE PROTRUDED THE ENGINE THRUST REVERSER SECTION AT THE APPROXIMATE 5 OCLOCK POSITION.  ENGINE REMOVED AND RELOCATED TO MFG. (K)                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA3EU    E6WE                 
20061020000012006102000001EA  2006       10         20         2006FA0000993    220061005G8530LW19001         EXHAUST VALVE                           CESSNA182   182T        2072703CE  LYC   O540  IO540AB1A5       EA  MCAULY3D36C B3D36C431   GL  NR 5 CYLINDER   STUCK           B  JRURK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL0717HP 997                    18281436    L2971648A   041547          DURING A PHASE 2 INSPECTION, CYLINDER NR 5 WAS FOUND TO HAVE LOW COMPRESSION (10/80) WITH A STRONG LEAK PASSED THE EXHAUST VALVE.  SUBSEQUENT INSPECTION FOLLOWING THE INSTRUCTIONS FOUND IN LYCOMING SB 388C REVEALED THAT THE EXHAUST VALVE WAS PARTIALLY STUCK AND WOULD NOT FULLY CLOSE.  THE EXHAUST VALVE ALSO COULD NOT BE REMOVED FROM THE CYLINDER ONCE THE CYLINDER WAS REMOVED FROM THE ENGINE.  LYCOMING RECOMMENDS THE FOLLOWING INTERVAL FOR INSPECTING NON-HELICOPTER ENGINES, "400 HOUR INTERVALS OR EARLIER IF VALVE STICKING IS SUSPECTED UNTIL EXHAUST VALVE GUIDES ARE REPLACED WITH GUIDES MADE OF IMPROVED MATERIAL (REFER TO LATEST REVISION OF SERVICE INSTRUCTION 1485)".                                              1H71 3O3  ONT3A13    1E4     5  C         
20061020000392006102000039EA  2006       10         20         2006FA0000995    220060609G8520                CRANKCASE                               MOONEYM20   M20E        5870212SW  LYC   O360  AEIO360A1A  41514EA                              ENGINE          BROKEN          P      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CLCLIMB          1                      WP09671DB     200               670030                                  WHEN OUR ENGINE NEEDED A MAJOR OVERHAUL THE CRANKCASE WAS SENT TO DIVCO IN TULSA, OKLAHOMA FOR INSPECTION AND FAA AIRWORTHINESS CERTIFICATION.  DIVCO DID REPAIRS AND MACHINE WORK AND CERTIFIED THE CRANKCASE AS AIRWORTHY ON FAA FORM 8130 PER 14 CFR  43.13 (B).  THE ENGINE WAS ASSEMBLED AND INSTALLED IN THE AIRPLANE.  AT JUST OVER 200 HOURS THE CRANKCASE NEARLY BROKE IN HALF AT DIVCO'S REPAIR.   IN A MATTER OF MINUTES THE ENGINE LOST SIX OF THE EIGHT QUARTS OF OIL IT HAD.  THE CRANKCASE BREAK AND A SUBSEQUENT ENGINE FAILURE COULD HAVE BEEN CATASTROPHIC!  THE TOTAL LOSS OF THE ENGINE, LOSS OF THE AIRPLANE AND LOSS OF LIFE OF THOSE ON BOARD AND ON THE GROUND WERE A VERY REAL POSSIBILITY.  FORTUNATELY, HAD JUST DEP1L71 3O3  O  2A3     1E10                 
20061020000362006102000036SO  2006       10         20         2006FA0000999    120061002G510234285           LINE                                    BALWKSFIRE  FIREFLY715  1050518SO                                                               FUEL SYS        SEPARATED       B  OG2RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE072203B2                      F7B2009                                 HOSE SEPARATED AT THE FUEL LINE END.  PILOT WAS INFLATING BALLOON WHEN THIS OCCURRED.  NEW HOSES WERE INSTALLED ON 7/27/2006.  THE BALLOON HAD BEEN FLOWN TWICE, WITH A TOTAL OF 2.0 HOURS ON NEW HOSES.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1B00         A14SO                        
20061023001582006102300158    2006       10         23         2006FA0001000    220061009G7314271T00687       PUMP                                    BOEING767   767*               NM                                                               ENGINE FUEL     CRACKED         B  DM4RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO19                                                                    PART HAS CRACK IN FILTER BOWL PORT, UNIT LEAKING.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA1NM                         
20061025001252006102500125    2006       10         25         2006FA0001001    420060927G3417FE422           RELAY                                   AMD   FALC50FALCON50MYST2730106EU  GARRTTTFE731TFE731*     01518WP                              AIR DATA        FAILED          B  XJRRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE09925BC                       257                                     LOSS OF RT AIR DATA ELECTRICAL POWER CAUSES A SNEAK PATH THROUGH THE ARTHUR Q AIR DATA REVERSION RELAYS ON RELAY CARD 417J.  THIS SNEAK PATH WILL CAUSE THE LT RADIO TUNING UNIT TO REVERT TO AIR DATA SOURCE NR 2.  BECAUSE AIR DATA SOURCE NR 2 IS NOW INACTIVE, NEITHER TRANSPONDER WILL HAVE ALTITUDE ENCODING.  ALTITUDE ENCODING SOURCE SELECTION VIA THE MODE SELECTOR SOURCE SELECTION WILL HAVE NO EFFECT, NOR WILL CHANGING SELECTED TRANSPONDER OR AIR DATA REVERSION SWITCH ON EITHER PILOTS SIDE.  THIS IS A SINGLE POINT OF FAILURE CAUSING LOSS OF ALL ALTITUDE ENCODING AND WILL ALSO CAUSE TCAS FAILURE.  INSTALLATION OF A STEERING DIODE IN THE ARTHUR Q REVERSION RELAY CIRCUIT WILL PREVENT THIS PROBLEM FROM OCCURRING.  T2L73 4F4  F  A46EU   E6WE                 
20061026001822006102600182CE  2006       10         26         2006FA0001002    120060906G3260SR008           DOWNLOCK SWITCH                         CESSNA560   560XL       2076702CE  PWA   545   PW545A           NE                              RT MLG          FAILED          C  CNQRO   OTHER                                                                                           N  FALSE WARNING                                                                 CLCLIMB          1                      CE07651QS4482                   5605251     DB0515                      AFTER TAKEOFF AND GEAR RETRACTION ALL GEAR LIGHTS WENT OUT.  APPROX 5-10 INTO FLIGHT, NOTICED RT GREEN GEAR LIGHT WAS ON.  NO OTHER ABNORMAL LIGHTS NOTED.  40 MINUTES LATER LIGHT EXTINGUISHED.  TROUBLESHOT SYS BY RIGING ALL DOWN LOCK SWITCH WIRING AND SWITCH MOUNTED TO RT GEAR ACTUATOR AND AFTER COLD SOAKING FOUND SWITCH SR008 (DOWNLOCK SWITCH) HAD A 2.209 M OHM READING WHEN OPEN (SHOULD BE NO READING).  REPLACED MLG ACTUATOR WITH A RENTAL UNIT AND OPERATIONAL CHECKS WERE GOOD.  RESERVICED EMERGENCY PNEUMATIC GEAR EXTENSION.  (K)                                                                                                                                                                                         2L72 4F4  FRTA22CE   E00059EN             
20061020000402006102000040CE  2006       10         20         2006FA0001003    120060919G243523085001        STARTER GEN                             BEECH 300   300BEECH    1152930CE  PWA   PT6   PT6A60A     52043NE  HARTZLHCB4M HCB4MP3     GL  LT ENGINE       WORN            B  AHTRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL11200VC1737 712               FL316                                   IN FLIGHT THE LT SIDE STARTER/GENERATOR AFT BEARING AT THE COOLING FAN FAILED AND THE GENERATOR FAILED.  THE AC RETURNED TO ITS DEPARTURE TERMINAL WITHOUT INCIDENT.  THE STARTER/GENERATOR WAS REPLACED AND THE CARGING AND ELECTRICAL SYSTEM OPS CHECKED GOOD.  NO KNOWN CAUSE, STARTER/GENERATOR WAS WITHIN THE 1000 HOURS FOR BEING OVERHAULED.  (K)                                                                                                                                                                                                                                                                                                                                                                                        2L72 4T4  T  A24CE   E4EA    6  CP56GL    
20061023001542006102300154WP  2006       10         23         2006FA0001004    220061009G72108964214         RESTRICTOR VALVE                        MTSBSIMU2   MU2B26      5780408CE  GARRTTTPE331TPE3310T         WP  HARTZLHCB4T HCB4TN5     GL  REDUCTION GB    FAILED          B  IZ2RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW15392P                        392SA       P105025C    CDA3129M1       FOLLOWING O/H AND INSTALLATION OF ENGINE ON AC AN IN-FLIGHT CHECK OF THE NTS SYSTEM WAS PERFORMED IAW MM INSTRUCTIONS.  UPON ACTUATION OF THE STOP SWITCH BY THE PILOT FOR THE LT ENGINE THE AC YAWED NOSE LT APPROXIMATELY 20 TO 25 DEGREES.  ALSO, THE ENGINE RPM HESITATED TO DECAY FOR 1 TO 2 SECONDS THEN DECAYED NORMALLY TO 35 PERCENT RPM.  TROUBLESHOOTING FOLLOWING FLIGHT SHOWED THAT THE (TRIP) PRESSURE OF THE ENGINE WAS HIGHER THAN NORMAL AND THE DECISION WAS MADE TO REPLACE THE TORQUE SENSOR ASSY PN 31017263.  A SECOND IN FLIGHT CHECK OF THE NTS SYSTEM WAS PERFORMED WITH THE SAME UNSATISFACTORY RESULTS.  FURTHER TROUBLESHOOTING IAW MM.  INSTRUCTION WAS CONDUCTED WITH NO DEFECTS NOTED.  ENGINE REDUCTION GEARBOX 1H72 3T4  TRTA10SW   E4WE    6  CP40EA    
20061020000972006102000097SW  2006       10         20         2006FA0001007    120060908G5340                TEE FITTING                             MOONEYM20   M20J        5870219SW  LYC   O360  IO360A1A    41514EA                              FUSELAGE        LOOSE           B  B2ERO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA235760Y721                    241635                                  DURING ANNUAL INSPECTION, FOUND PRECISE FLIGHT SVS V, SN 17245 (T-FITTING) LOOSE IN HOUSING.  IF FITTING PULLED OUR YOU WOULD HAVE COMPLETE VACUUM SYS FAILURE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L71 3O3  O  2A3     1E10                 
20061023001572006102300157EA  2006       10         23         2006FA0001008    120061002G2740                CONTROL UNIT                            CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              HORIZONTAL STAB MALFUNCTIONED   B      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW0587353                       7353                                    REPORTED IN-FLIGHT SQUAWK, (STAB TRIM FAIL IN FLIGHT) ON AC.  HSTCU WAS REMOVED AND SENT FOR TEST AND REPAIR.  DURING BENCH TEST/INSPECTION THE FOLLOWING ITEMS WERE NOTED.  UNIT MEMORY INDICATED (CP PITCH TRIM SWITCH JAMMED) (AC SWITCH).  DURING AUTO TEST, (HSTCU DOOR SWITCH (PN 134-30901-005) FAILED) WAS INDICATED.  DISASSY AND INSPECTION REVEALED SMALL AMOUNT OF CORROSION ON CIF ASSY OF HSTCU.  PROBABLE CAUSES/RECOMMENDATIONS:  KNOWN PROBLEM-UNRELIABLE TRIM SWITCH HAS A DOCUMENT THAT ADDRESSES THIS ISSUE.  HSTCU DOOR SWITCH PROBABLY BENT AFTER INCIDENT DURING TROUBLESHOOTING, IF PRIOR TO FLIGHT FAULT WOULD HAVE BEEN INDICATED IN COCKPIT/CAUTION MECHANICS TO AVOID BENDING SWITCH ARM DURING MAINTENANCE ACTIONS.2L72 4F4  FRTA21EA   E15NE                
20061020000242006102000024SO  2006       10         20         2006FA0001009    220060923G7322MA35PA          CARBURETOR                              CESSNA150   150C        2071808CE  CONT  O200  O200*       17020SO                              ENGINE          FAILED          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP157870Z                       15059970    250066A48                   ENGINE STOPPAGE ON FINAL DUE TO CARBURATOR FLOODING, SUSPECT STUCK FLOAT.  REMOVED UNIT AND SENT BACK TO MANUFACTURE FOR INSPECTION.  THIS CARBURETOR WAS (FACTORY REBUILT) 1 YEAR EARLIER AND HAD LESS THAN 55 HOURS TT.  FUEL WAS FOUND SPILLING OUT OF COWLING WHEN EXITING THE AIRCRAFT, SHUT FUEL VALVE OFF.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3O3  O  3A19    E252                 
20061020000302006102000030SO  2006       10         20         2006FA0001010    120060913G510089307000        ROD END                                 PIPER PA28  PA28R200    7102811SO  LYC   O360  IO360C1C    41514EA                              CONTROL CABLE   BROKEN          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP0755068                       28R7335176  L1061351A                   ROD END BROKE AT POINT OF ATTACHMENT ON SERVO ARM.  APPEARS BOLT MAY HAVE BEEN OVER TORQUED AT SOME POINT WHICH CAUSED A STRESS CRACK AND FAILURE OF BOLT AT POINT OF ATTACHMENT.  TORQUE BOLT AT TIME OF INSTALLATION.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L71 3O3  O  2A13    1E10                 
20061023001592006102300159SO  2006       10         23         2006FA0001011    220060925G8530AEC631397CN2C   CYLINDER                                BEECH 36    A36         1151604CE  CONT  O550  IO550B           SO                              ENGINE          DAMAGED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO094307S133                    E675        281757                      THE DEFECTS WERE NOTED ON 6 ENGINE COMPONENTS, CYLINDERS WITH 133.1 SINCE NEW AND PUT IN SERVICE ON THE SAME ENGINE DECEMBER 2004.  NR 4 AND NR 5 CYLINDERS WERE CRACKED IN THE EXHAUST PORT WITH A HOLE BURNED THROUGH AT THE CRACK AND WAS LEAKING EXHAUST GASSES OVERBOARD.  NR1, NR2, NR3, AND NR6 CYLINDERS WERE CRACKED IN THE SAME LOCATION AS NR4 AND NR5.  THE CRACKS ARE IB OF THE EXHAUST PORT APPEARS TO BE TOO THIN AND NOT ABLE TO WITHSTAND THE HEAT AND STRESS PRESENT DURING NORMAL ENGINE OPERATION.  (K)                                                                                                                                                                                                                     1L71 3O3  O  3A15    E3SO                 
20061023001602006102300160EA  2006       10         23         2006FA0001012    220061011G8500AEL13884        MAIN BEARING                                                               LYC   O320  O320B2B     41508EA                              ENGINE          FAILED          B  O3ORO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      AL03     251                                RL1362339A                  THIS ENGINE WAS DISMANTLED DUE TO METAL CONTAMINATION.  WE DISCOVERED THAT THE REAR SURFACE OF THE BEARING WAS PEELING AWAY.  PROBABLE CAUSES OF THIS BEARING FAILURE ARE UNKNOWN.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                3  O          E274                 
20061026001842006102600184EA  2006       10         26         2006FA0001013    220061009G8550                VALVE GUIDE                             CESSNA182   182T        2072703CE  LYC   O540  IO540AB1A5       EA                              ENGINE          LEAKING         B  LC1RO   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      EA07168TA                       18281068    L2822248A                   OPERATOR COMPLAINED OF AN OIL LEAK.  WHEN COWL WAS REMOVED IT WAS OBVIOUS THAT THE NR3 AND NR4 EXHAUST PUSH RODS AND PUSH ROD HOUSING WERE BENT.  SUSPECTED STICKING EXHAUST VALVES.  EXHAUST VALVE TO GUIDE CLEARANCE WAS CHECKED ON ALL CYLINDERS IAW SB AND THE PROBLEM CYLINDERS CHECKED OK.  CYLINDERS NR2 AND NR5 CHECKED BELOW THE SPECIFIED CLEARANCE.  INSPECTED THE LIFTERS ASSOCIATED THE DAMAGED PUSH RODS AND FOUND NO OTHER PROBLEMS.  ALL EXHAUST VALVE GUIDES WERE REAMED IAW SI 1425A, AND EXHAUST VALVE STEMS WERE CLEANED PRIOR TO REASSEMBLY.  (K)                                                                                                                                                                          1H71 3O3  ONT3A13    1E4                  
20061023001552006102300155SO  2006       10         23         2006FA0001014    120061011G261223454G10        FIRE LOOP                               CURTISC46   C46RCURTIS  2622710SO  PWA   R2800 R280097     52026NE  HAMSTD34E   34E60       NE  NR 2 NACELLE    DAMAGED         B  EVARO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      AL017848B                       273                                     FIRE WARNING LIGHT NR 2 ENGINE ZONE 2 AND 3 ILLUMINATED THEN EXTINGUISHED.  VISUAL INSPECTION OF ENGINE SHOWS NO SIGN OF FIRE OR DAMAGE, SUSPECT FAULTY LOOP DETECTOR.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4R4  R  3A2     E231    6  CP881     
20061020000252006102000025SO  2006       10         20         2006FA0001015    120061019G5320AN78310D        TEE FITTING                             GULSTMG1159 G1159       3953505SO                                                               BULKHEAD        CRACKED         E      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO19750RA*                      117                                     UPON POST FLIGHT INSPECTION THE PILOT NOTICED SMALL AMOUNT OF HYDRAULIC FLUID SEEPING FROM THE BOTTOM OF THE RADOME.  MAINTENANCE DETERMINED THAT THE LEAK WAS COMING FROM A BULKHEAD TEE IN THE NOSE LANDING GEAR DUMP VALVE LINE.  THE LEAK WAS INITIALLY THOUGHT TO BE CAUSED BY A DEFECTIVE PACKING BETWEEN THE TEE AND A REDUCER INSTALLED IN THE FEMALE PORT OF THE TEE.  THE PACKING WAS RENEWED AND THE SYSTEM WAS LAEK CHECKED.  THE LEAK PERSISTED,THE TEE FITTING WAS REMOVED AND INSPECTED.  A CRACK WAS FOUND ON THE INNER BORE OF THE FEMALE PORT OF THE FITTING AT THE MOLD LINE OF THE FITTING.  THE CRACK WAS NOT VISIBLE ON THE EXTERIOR OF THE TEE.  THE TEE WAS REPLACED.THE SYSTEM WAS LEAKED CHECKED AND THE AIRCRAFT WAS 2L72 4F    RTA12EA                        
20061020000292006102000029CE  2006       10         20         2006FA0001016    120061019G5710                STRUCTURE                               CESSNA500   550         2076604CE                                                               RT WING         CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW011254X9937 300               0494                                    DURING A PHASE NR 5 A CRACH WAS FOUND IN THE LT & RT WHEEL WELL AREA ADJACENT TO THE INSIDE CORNER OF THE OPENING AT THE WHEEL WELL. A REPAIR WAS DONE AS PER SERRIA INDUSTRIES WING SKIN REPAIR ENGINEERING REPORT NR 3521-36 AND A DER 8110-3. THIS REPAIR HAS BEEN DONE ON SEVERAL OF OUR (26) AIRCRAFT AND IS NOT UNCOMMON TO SEE IN THE FIELD. I WOULD LIKE TO SEE CESSNA TO COME OUT WITH A SB KIT FOR THIS FIX FOR US IN THE FIELD RATHER THAN HAVING TO GET DER SUPPORTON OUR OWN.                                                                                                                                                                                                                                                      1L72 4F      A22CE                        
20061129003802006112900380SW  2006       11         29         2006FA0001017    120061020G5302205030889015S   SUPPORT BRACKET                         BELL  204   UH1H        1181407SW                                                               TAILBOOM        LOOSE           C      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW99                                                                    TAIL BOOM ELEVATOR SUPPORT BRACKET LOOSE. (WORKING RIVETS/SITE OF PREVIOUS REPAIR WITH PULL TYPE RIVETS).                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1G71 4U      EXPA1G71                     
20061023001532006102300153SO  2006       10         23         2006FA0001018    120061020G28222B663OH         PUMP                                    PIPER PA31  PA31325     7103105SO  LYC   O540  TIO540J2BD  41532EA                              FUEL BOOST      FAILED          B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE0122GE      766               317712091   RL1182161A                  LT FUEL BOOST PUMP FAILED ON RUNUP, DEBRIS CONTAMINATED FUEL SYSTEM, DAMAGED ENGINE DRIVEN FUEL PUMP, FUEL FLOW TRANSDUCER, CONTAMINATION FOUND IN FUEL SERVO FUEL INLET SCREEN.  SERVO REMOVED AND SENT TO REPAIR FACILITY FOR INSPECTION AND OR REPAIRS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L72 3O3  O  A20SO   E14EA                
20061025001262006102500126GL  2006       10         25         2006FA0001020    120061018G2820                LINE                                    CIRRUSSR    SR20        05628AJGL  CONT  IO360 IO360*      17025CE                              FUEL SYSTEM     CHAFED          B      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL21777ND                       1258                                    FUEL LINE CHAFED, LINE REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L71 3O3  ONTA00009CHE1CE                 
20061106000552006110600055CE  2006       11         6          2006FA0001021    120061006G3230991242339       VALVE                                   CESSNA525   525         2076601CE  WILINTFJ44  FJ44        66000GL                              MLG             MALFUNCTIONED   B  CNQ3O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL13122CS                       5250469                                 CREW REPORTED (HYDRAULIC PRESSURE ON) LIGHT STAYED ILLUMINATED AFTER LANDING GEAR RETRACTION.  REPLACED LOADING VALVE AND OPERATIONALLY CHECKED HYDRAULIC SYSTEM.  AIRCRAFT WAS RETURNED TO SERVICE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 4F4  FRTA1WI    E3GL                 
20061026001612006102600161CE  2006       10         26         2006FA0001022    120061006G5610NP13972112      WINDSHIELD                              CESSNA750   750         2076810CE  ALLSN AE3007AE3007C          GL                              COCKPIT         FAILED          B  CNQ3O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL137SB                         7500209                                 RT WINDSHIELD OUTER PANE FAILED IN FLIGHT.  THE OUTER PANE IS NON STRUCTURAL AND DID NOT EFFECT THE INTEGRITY OF THE PRESSURE VESSEL.  WINDSHIELD WAS SENT TO MFG ENGINEERING FOR FAILURE EVALUATION. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4J4  FRTT00007WITE6CH                
20061026001602006102600160CE  2006       10         26         2006FA0001023    120061006G2910991242339       VALVE                                   CESSNA525   525         2076601CE  WILINTFJ44  FJ44        66000GL                              HYD SYSTEM      FAILED          B  CNQ3O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL13122CS                       5250469                                 CREW REPORTED ALL HYDRAULIC SYSTEMS INOPERATIVE IN FLIGHT.  LANDING GEAR WAS EXTENDED PNEUMATICALLY AND AIRCRAFT LANDED WITHOUT INCIDENT.  IT WAS DETERMINED THE HYDRAULIC LOADING VALVE WAS NOT CLOSING ALLOWING HYDRAULIC PRESSURE TO BUILD.  THE HYDRAULIC LOADING VALVE WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                         1L72 4F4  FRTA1WI    E3GL                 
20061026001672006102600167WP  2006       10         26         2006FA0001024    220061002G7250                TURBINE WHEEL                           RAYTHNDH125 HAWKER800XP 7150012CE  GARRTTTFE731TFE7315BR        WP                              NR 2 ENGINE     FRACTURED       B  ROIRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL136NR  679                    258701      P107953                     IN FLIGHT, CREW FELT SLIGHT TO MODERATE VIBRATION FROM NR 2 ENGINE.  AFTER LANDING FURTHER INSPECTION FOUND APPROX ONE INCH OF ONE OF THE 3 LPT DISK BLADES MISSING.  REASON FOR FAILURE AT THIS TIME UNDER INVESTIGATION BY MFG, SB 72-3689.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F4  FRTA3EU    E6WE                 
20061025001292006102500129NE  2006       10         25         2006FA0001025    220061003G723030B47451        COMPRESSOR WHEEL                        LEAR  60    60LEAR      5170707CE  PWA   305   PW305A      52128NE                              LT ENGINE       CRACKED         B  BTVRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL23699DA2054                   237         PCECA0319                   (REF NR: 6841.5.30) DURING A SCHEDULED INSPECTION, EDDY CURRENT NDT REVEALED A CRACK IN THE LT ENGINE HP COMPRESSOR STAGE 1 ROTOR.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRTA10CE   E35NE                
20061026001782006102600178SO  2006       10         26         2006FA0001027    220061017G8520                ROD                                     BEECH 58    58          1152740CE  CONT  O520  IO520C      17032SO                              ENGINE          FAILED          D      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      SW11640LS907                    TH1107      827255R                     CYLINDER NR 2 PISTON ROD FAILED WHILE AIRCRAFT WAS IN CRUISE FLIGHT. PROP WAS FEATHERED. AIRCRAFT LANDED WITHOUT INCIDENT. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L72 3O3  O  3A16    E5CE                 
20061026001592006102600159CE  2006       10         26         2006FA0001028    120060912G6100A4564           BEARING                                 CESSNA208   208B        2073701CE  PWA   PT6   PT6*        52043EA  MCAULY3AF34C3GFR34C703  GL  PROPELLER       BROKEN          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA27324SJ1898                   208B0908                010761          UPON DISASSEMBLY OF THIS PROPELLER IAW WITH MFG TECH REPORT NR940. IT WAS DISCOVERED THAT THE PITCH CHANGE LINK BUSHINGS, P/N A4564, ON BLADES NR 2 AND NR 3 WERE BROKEN AND PARTIALLY MISSING. AT LEAST 50 PERCENT OF THE BUSHINGS WERE NOT IN THE LINK. THE THICKNESS OF BUSHING WOULD ALLOW THE BLADE ANGLES OF TWO OF THE THREE BLADES TO BE MUCH DIFFERENT ANGLE THAN THEY SHOULD BE, LEADING TO EXCESSIVE VIBRATION AND LOSS OF EFFICIENCY. (THIS WAS THE REASON FOR THE HIGHER VIBRATIONS REPORTED BY THE FLIGHT CREWS). SB137AB HAS A MANDATORY SPECIFIED TIME BETWEEN OVERHAULS FOR THIS PROPELLER OF 4000 HOURS OR 72 CALENDAR MONTHS, WHICHEVER COMES FIRST. THIS PROPELLER WAS REMOVED DUE TO A CALENDAR CHANGE, NOT DUE TO HOURS IN1H71 3T3  T  A37CE   E2NE    5  CP60GL    
20061026001632006102600163CE  2006       10         26         2006FA0001029    120061009G5280634100616       STUD            CESSNA                  CESSNA525   525         2076601CE  WILINTFJ44  FJ44        66000GL                              MLG DOOR        BROKEN          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE01902GW488                    5250553                                 COMPONENT STUD APPEARS TO HAVE BEEN CRACKED FOR SOME TIME, RUST EVIDENT HALF WAY THRU BOLT CROSS SECTION AT THE START OF THE THREADED AREA, NEAR CENTER OF THE STUD. COULD POSSIBLY HAVE BEEN CAUSED BY MFG FLAW, OVER TORQUEING OF SAFETY JAMB NUTS, TO OVER RIGGING OF MLG DOOR (TOO TIGHT), IN THE GEAR UP POSITION. WHEN THIS LINK BREAKS, THE DOOR DROPS FURTHER THAN THE GEAR ALLOWING IT TO COME INTO CONTACT WITH THE GROUND DAMAGING THE GEAR DOOR, WHICH UNDER THE RIGHT CIRCUMSTANCE COULD CAUSE EXTENSIVE DAMAGE TO THE WING. (K)                                                                                                                                                                                                   1L72 4F4  FRTA1WI    E3GL                 
20061026001652006102600165EA  2006       10         26         2006FA0001030    220061019G8530LW19001         EXHAUST VALVE                                                              LYC   O320  O320E2D     41508EA                              CYLINDER NR 3   BROKEN          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW99     1606                                                           HEAD OF THE NR 3 EXHAUST VALVE BROKE OFF DURING ENGINE OPERATION. THE BROKEN PIECES DAMAGED THE PISTON AND CYLINDER HEAD AS WELL AS THE LOWER SPARK PLUG. SMALL PIECES FOUND IN THE OTHER 3 CYLINDERS AS WELL. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     3  O          E274                 
20061031001562006103100156CE  2006       10         31         2006FA0001031    120060803G7430A5109           IGNITION SWITCH                         CESSNA172   172S        2072439CE                                                               INSTRUMENT PANELINTERMITTENT    D      D   RETURN TO BLOCK                                                                                 O  OTHER                                                                         TXTAXI/GRND HDL  1                      GL03656SJ1098                   172S8656                                DURING A GROUND OUT CHECK OF THE IGNITION SWITCH, THE ENGINE CONTINUED TO RUN.  REPEATED TESTS DUPLICATED CONDITION 4 OUT OF 10 TIMES.  UPON FURTHER INVESTIGATION IT WAS FOUND THAT THE RT MAGNETO CONTINUED TO RUN WHEN THE FAULT OCCURRED.  REPLACED THE MAGNETO/STARTER SWITCH.  MAGNETO SWITCH, MODEL NR A-510-9.  AC PN C292501-0107, CAGE NR 65873.                                                                                                                                                                                                                                                                                                                                                                                      1H71 3O    NT3A12                         
20061031001642006103100164CE  2006       10         31         2006FA0001032    120061025G3240656120011       TIE ROD                                 CESSNA500   560CESSNA   2076750CE  PWA   530   PW535A           NE                              LEFT            CHAFED          D      K   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      WP27221VP2161                   5600585                                 LT BRAKE TIE-ROD CHAFING ON COCKPIT DEFROST DUCT APPROX 6 INCHES ABOVE COCKPIT FLOOR, ROD WORN APPROX .030 INCHES.  NO RELOCATION OF COMPONENTS POSSIBLE TO ALLEVIATE CHAFING.  REPLACEMENT PART RECEIVED FROM MFG IS DIFFERENT PN AND SMALLER DIAMETER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F4  FRTA22CE   E00053EN             
20061031001652006103100165CE  2006       10         31         2006FA0001033    120061030G7160NONEREADABLE    AIR FILTER                              CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              ENGINE          DETERIORATED    B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO152108L66   39                172S9605                                METAL PIECES COMING OFF AIRFILTER (AIR FILTER P/N: CPE1173, PREVIOUSLY INSTALLED IAW STC NR SA01669CH. THE METAL PIECES THAT ARE COMING A PART ARE LOCATED ON THE TOP, FRONT AND REAR OF THE FILTER ASSEMBLY.  AN FAA-PMA STAMP COVERS THE PN ON THE FILTER. THE ONLY IDENTIFYING FEATURES ON THE FILTER IS A K&N STAMP, AND A MESSAGE TO SERVICE AT 50,000 MILES.                                                                                                                                                                                                                                                                                                                                                                              1H71 3O3  ONT3A12    1E10                 
20061031001692006103100169SO  2006       10         31         2006FA0001034    220061027G8550ES48108         OIL FILTER                              CESSNA140   140         2071602CE  CONT  C85   C8512F      17008SO                              ENGINE          CONTAMINATED    C      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CE07729512                      10149                                   DURING CRUISE FLIGHT, OIL PRESSURE DROPPED TO BELOW MINIMUM REDLINE.  PRECAUTIONARY LANDING WAS MADE.  ON INSPECTION, DISCOVERED RECENTLY INSTALLED (2 HOURS IN SERVICE) OIL FILTER HAS DESIGN AND/OR MANUFACTURING DEFECT ALLOWING AN INTERNAL SEAL TO BE DAMAGED DURING MFG SUCH THAT RUBBER SEAL MATERIAL IS RELEASED FROM THE FILTER INTO THE ENGINE OIL.  LOW OIL PRESSURE CONDITION WAS DUE TO A CHUNK OF THIS MATERIAL FOULING THE SEAT OF THE OIL PRESSURE REGULATING VALVE, KEEPING THE VALVE PARTIALLY OPEN.  THE FILTER HAS BEEN DISSECTED AND I HAVE DIGITAL PHOTOS OF THE PARTS IN QUESTION AS WELL AS THE DEBRIS FOUND IN THE OIL SYSTEM.  I WILL RETAIN CUSTODY OF THE PARTS, BUT I CAN MAKE THEM AVAILABLE FOR INSPECTION AT THE1H71 3O3  ONCA768    E233                 
20061031001702006103100170SO  2006       10         31         2006FA0001035    220061027G8550ES48108         OIL FILTER                              CESSNA140   140         2071602CE  CONT  C85   C8512F      17008SO                              ENGINE          CONTAMINATED    C      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CE07729512                      10149                                   DURING CRUISE FLIGHT, OIL PRESSURE DROPPED TO BELOW MINIMUM REDLINE.  PRECAUTIONARY LANDING WAS MADE.  ON INSPECTION, DISCOVERED RECENTLY INSTALLED (2 HOURS IN SERVICE) OIL FILTER HAS DESIGN AND/OR MANUFACTURING DEFECT ALLOWING AN INTERNAL SEAL TO BE DAMAGED DURING MFG SUCH THAT RUBBER SEAL MATERIAL IS RELEASED FROM THE FILTER INTO THE ENGINE OIL.  LOW OIL PRESSURE CONDITION WAS DUE TO A CHUNK OF THIS MATERIAL FOULING THE SEAT OF THE OIL PRESSURE REGULATING VALVE, KEEPING THE VALVE PARTIALLY OPEN.  THE FILTER HAS BEEN DISSECTED AND I HAVE DIGITAL PHOTOS OF THE PARTS IN QUESTION AS WELL AS THE DEBRIS FOUND IN THE OIL SYSTEM.  I WILL RETAIN CUSTODY OF THE PARTS, BUT I CAN MAKE THEM AVAILABLE FOR INSPECTION AT THE1H71 3O3  ONCA768    E233                 
20061101000952006110100095SW  2006       11         1          2006FA0001036    120061031G6320206033426001    SUPPORT         BELL                    BELL  206   206L3       1182108SW  ALLSN 250C  250C30      03013GL                              TAILBOOM        CRACKED         B  SL3RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NE01812TV3622 50    AO1402      51185                                   CRACK FOUND AT TAIL ROTOR GEARBOX AFT LT MOUNTING HOLE ON TAILBOOM CASTING. REPLACED GEARBOX SUPPORT CASTING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1G71 3U3  U  H2SW    E1GL                 
20061117001462006111700146EA  2006       11         17         2006FA0001037    220061101G8530LW19001         EXHAUST VALVE                           CESSNA182   182S        2072701CE  LYC   O540  IO540AB1A5       EA  MCAULY3D36C B3D36C431   GL  ENGINE          STUCK           B  JRURK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL07311HP673                    18280919    RL2144048A  002157          DURING A PHASE 2 INSPECTION, CYLINDER NR 5 WAS FOUND TO HAVE LOW COMPRESSION (5/80) WITH A STRONG LEAK PASSED THE EXHAUST VALVE. SUBSEQUENT INSPECTION FOLLOWING THE INSTRUCTIONS FOUND IN SB 388C REVEALED THE CYLINDER DID NOT MEET THE MEASUREMENT CRITERIA FOR THE EXHAUST VALVE GUIDE. THE MEASUREMENT TAKEN BEFORE REAMING (IAW SB388C) WAS .007 INCH.  THE EXHAUST VALVE WAS REMOVED FROM THE CYLINDER (WITH THE CYLINDER INSTALLED) AND EXHAUST VALVE GUIDE WAS REAMED. A COMPRESSION CHECK WAS TAKEN AGAIN ON CYLINDER NR 5 AND COMPRESSION AFTER REAMING WAS 77/80.  MEASUREMENT AFTER REAMING WAS .0175 INCH. THE PERMISSIBLE RANGE IS .015 TO .030 INCH.  CYLINDER NR 3 ALSO FAILED THE MEASUREMENT CRITERIA OF SB 388C. THIS EXHAUS1H71 3O3  ONT3A13    1E4     5  C         
20061107000652006110700065CE  2006       11         7          2006FA0001039    120061011G323399121202        SWITCH                                  CESSNA500   560CESSNA   2076750CE  PWA   JT15  JT15D5      52112NE                              NOSE GEAR ACTUATMALFUNCTIONED   D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA6194TX 3104                   5600247                                 NOSE GEAR ACTUATOR JAMMED IN THE EXTENDED POSITION.  WOULD NOT RETRACT.  FOUND ACTUATOR FAULTY INTERANA SWITCH.  REPLACED NOSE GEAR ACTUATOR.  ACTUATOR PARET NR 15232005, SN 842.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRTA22CE   E25EA                
20061107000662006110700066NE  2006       11         7          2006FA0001040    220061005G7320310033501       SENSOR                                  BEECH MU300 400A        1155402CE  PWA   JT15  JT15D5      52112NE                              LT ENGINE N1    DAMAGED         B  AHTRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL11827SB8181 406               RK2         PCE100183                   IN NORMAL FLIGHT, THE EFC OFF(ELECTRONIC FUEL CONTROL) ANNUNCIATOR LIGHT ILLUMINATED.  THE PILOTS ATTEMPTED TO RESET THE EFC SEVERAL TIMES, FAILING AT EVERY ATTEMPT.  TROUBLESHOOTING REVEALED DAMAGE TO THE N1 SENSOR PROBE CAUSED BY THE N1 PICK-UP, AT 24 EQUALLY-SPACED TOOTHED WHEEL INTEGRAL TO THE COMPRESSOR SHAFT.  MINUTE DAMAGE WAS INFLICTED ON THE PROBE, CONSISTING OF AN EXTREMELY SHALLOW GROOVE CUT INTO THE END OF THE PROBE.   THE TOOTHED WHEEL DID NOT APPEAR DAMAGED.  THE PROBE WAS PROBABLY DAMAGED DUE TO THE IMPROPER INSTALLATION.  (K)                                                                                                                                                                             2H72 4F4  FRTA16SW   E25EA                
20061107000642006110700064SW  2006       11         7          2006FA0001041    120061006G6200069A5512        DRIVE BELT                              HUGHES269   269C1       8059504SW  LYC   O360  HIO360*     41514EA                              MAIN ROTOR      STRETCHED       B  HA4RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO1517535                       0225                                    NEW DRIVE BELTS WERE INSTALLED, STRETCHED FOR 24 HOURS, AND RE-ADJUSTED IAW MM.  THE AIRCRAFT WAS RETURNED TO SERVICE AND .5 HOUR INTO THE FIRST FLIGHT THE PILOT NOTICED THE MAIN ROTOR RPM DECAYING AND ENGINE RPM INCREASING.  A STEEP DESCENT WITH POWER WAS PERFORMED AND THE AIRCRAFT LANDED SAFELY.  A SUBSEQUENT MAINTENANCE INSPECTION REVEALED THAT THE BELTS HAD CONTINUED TO STRETCH AFTER THE AIRCRAFT WAS RETURNED TO SEVERICE CAUSING THE CLUTCH ACTUATOR TENSION TO BECOME EXCESSIVELY LOOSE.  THIS ALLOWED THE BELTS TO SLIP ON THE DRIVE PULLEYS AND ALLOWED THE MAIN ROTOR RPM TO DROOP.  (K)                                                                                                                                1G71 3O3  OO 4H12    1E10                 
20061107000572006110700057NM  2006       11         7          2006FA0001042    120061015G5330                SKIN                                    BOEING727   727191      1384063NM  PWA   JT8   JT8D7B      52053NE                              BS 360 S24-26R  CORRODED        B  KO0RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL23502MG                       19391                                   CORROSION ON FUSELAGE SKIN AT BS 360 CIRCUMFERENTIAL SKIN JOINT BETWEEN STR 24R AND STR 26R.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L73 4F4  F  A3WE    E2EA                 
20061107000682006110700068NM  2006       11         7          2006FA0001043    120061015G5330                SKIN                                    BOEING727   727191      1384063NM  PWA   JT8   JT8D7B      52053NE                              BS 441 S17R     CORRODED        B  KO0RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL23502MG                       19391                                   CORROSION ON FUSELAGE SKIN AT BS 441, STR 17R.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L73 4F4  F  A3WE    E2EA                 
20061107000582006110700058NM  2006       11         7          2006FA0001044    120061015G551165174375        RIB                                     BOEING727   727191      1384063NM  PWA   JT8   JT8D7B      52053NE                              HORIZONTAL STAB CRACKED         B  KO0RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL23502MG                       19391                                   LT HORIZONTAL STABILIZER ELEVATOR HINGE SUPPORT RIB CRACKED (2.5 INCHES) ON OB, UPPER, AFT SIDE OF RIB AT ELEV STA 99.79.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L73 4F4  F  A3WE    E2EA                 
20061107000602006110700060NM  2006       11         7          2006FA0001045    120061015G5511651742812       RIB                                     BOEING727   727191      1384063NM  PWA   JT8   JT8D7B      52053NE                              HORIZONTAL STAB CRACKED         B  KO0RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL23502MG                       19391                                   RT HORZ STAB ELEVATOR HINGE SUPPORT RIB CRACKED (2.5 INCH) ON UPPER FLANGE AT ELEV STA 17.20.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L73 4F4  F  A3WE    E2EA                 
20061107000612006110700061NM  2006       11         7          2006FA0001046    120061015G5330                SKIN                                    BOEING727   727191      1384063NM  PWA   JT8   JT8D7B      52053NE                              BS 480 S7-8L    CORRODED        B  KO0RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL23502MG                       19391                                   EXTERNAL FUSELAGE SKIN CORRODED AT STA 480, STR 7L TO STR 8L, CIRCUMFERENTIAL JOINT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L73 4F4  F  A3WE    E2EA                 
20061107000672006110700067NM  2006       11         7          2006FA0001047    120061015G5330                SKIN                                    BOEING727   727191      1384063NM  PWA   JT8   JT8D7B      52053NE                              BS 480 S9-10L   CORRODED        B  KO0RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL23502MG                       19391                                   EXTERNAL FUSELAGE SKIN CORRODED AT STA 480, STR 9L TO STR 10L, CIRCUMFERENTIAL JOINT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L73 4F4  F  A3WE    E2EA                 
20061107000422006110700042SW  2006       11         7          2006FA0001048    120061003G3220540004          LEG ASSY                                MOONEYM20   M20C        5870208SW  LYC   O360  O360*       41514EA                              NLG ASSY        DAMAGED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE0178880                       2895                                    NOSE GEAR COLLAPSED UPON LANDING.  INITIAL INSPECTION FOUND BOTH TUBES ON THE NOSE GEAR LEG ASSEMBLY BROKEN.  RETRACT MECHANISM TUBES BENT.  UNABLE TO DETERMINE WHICH COMPONENTS WERE DAMAGED PRIOR TO THE INCIDENT.  PILOT REPORTED THAT THE LANDING GEAR WAS HARDER THAN NORMAL TO RETRACT DURING THE LAST TAKEOFF AND EASIER TO EXTEND THAN NORMAL DURING THIS LANDING.  (K)                                                                                                                                                                                                                                                                                                                                                                1L71 3O3  O  2A3     E286                 
20061107000562006110700056GL  2006       11         7          2006FA0001049    120061010G2810C36L            CAP                                     DIAMONDA40  DA40        2990002GL                                                               FUEL TANK       LEAKING         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM07416FP40                     40FC016                                 UPON PREFLIGHT OF THE AIRCRAFT, AND AFTER SITTING OUTSIDE OF THE HANGAR DURING A RAINSTORM, 2 TO 3 SUMP GLASSES WERE FILLED WITH WATER FROM EACH WING FUEL TANK SUMP DRAIN.  FURTHER INSPECTION OF 9 OTHER AIRCRAFT OF THE SAME MAKE AND MODEL FOUND 2 OTHER AIRCRAFT WITH SIMILAR AMOUNTS OF WATER IN THE SUMP DRAINS.  ALL 3 OF THESE AIRCRAFT WERE TIED DOWN OUTSIDE DURING WEATHER ABOVE STATED.  INSPECTION OF THE FUEL FILLER FLANGE/CAP ASSEMBLY OF ALL TWELVE AIRCRAFT REVEALED THE SAME LOOSE FUEL CAP CONDITION.  ALL AIRCRAFT FUEL CAPS WERE TIGHTEN AS A PRECAUTION.  THE O-RING SEALS DID NOT APPEAR TO BE DAMAGED.                                                                                                                1L71 3O    NTA47CE                        
20061107000542006110700054EA  2006       11         7          2006FA0001050    220061025G8597DA424064100     WIRE HARNESS                            DIAMONDA40  DA40        2990002GL  LYC   O360  O360A4M     41514EA                              ALT/CB          DAMAGED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM07417FP69                     40FC017                                 TOTAL ELECTRICAL SYSTEM FAILURE IN FLIGHT.  INSPECTION REVEALED THAT THE MAIN POWER WIRES RING TERMINAL TO THE ALTERNATOR HAD FAILED CAUSING ARCING WHICH SHORTED THE ALTERNATOR OUT AND CAUSED THE MAIN AND ESSENTIAL BUSS CIRCUIT BREAKERS TO POP.  POSSIBLE CAUSE IS TOO SHORT OF A WIRE HARNESS WHICH DOES NOT ALLOW FOR ENGINE VIBRATION.  REMEDIED WITH NEW ALTERNATOR AND NEW ALTERNATOR CABLE ASSY PROVIDED BY MFG.  THE NEW CABLE ASSY IS A COUPLE OF INCHES LONGER TO PREVENT THIS FROM OCCURRING.  (K)                                                                                                                                                                                                                              1L71 3O3  ONTA47CE   E286                 
20061107000552006110700055GL  2006       11         7          2006FA0001051    120061010G2701D4122131200     CONTROL STICK                           DIAMONDA40  DA40        2990002GL                                                               CONTROL COLUMN  DAMAGED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM07418FP34                     40FC018                                 PILOTS CONTROL STICK GRIP BECAME LOOSE AND WOULD, IF PULLED ON, COULD BECOME DETACHED FROM THE CONTROL ASSEMBLY.  CHECK BOTH CONTROL GRIPS FOR LOOSE INSTALLATION AND REATTACH WITH APPROVED ADHESIVE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L71 3O    NTA47CE                        
20061107000532006110700053GL  2006       11         7          2006FA0001052    120061010G2810C36L            CAP                                     DIAMONDA40  DA40        2990002GL                                                               WING FUEL TANK  LEAKING         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM07420FP                       40FC020                                 UPON PREFLIGHT OF THE AIRCRAFT, AND AFTER SITTING OUTSIDE OF THE HANGAR DURING A RAINSTORM, 2 OR 3 SUMP GLASSES WERE FILLED WITH WATER FROM EACH WING FUEL TANK SUMP DRAIN.  FURTHER INSPECTION OF 9 OTHER AC OF THE SAME MAKE AND MODEL FOUND 2 OTHER AC WITH SIMILAR AMOUNTS OF WATER IN THE SUMP DRAINS.  ALL 3 OF THESE AC WERE TIED DOWN OUTSIDE DURING WEATHER ABOVE STATED.  INSPECTION OF THE FUEL FILLER FLANGE/CAP ASSY ON ALL 12 AIRCRAFT REVEALED THE SAME LOOSE FUEL CAP CONDITION.  ALL AC FUEL CAPS WERE TIGHTENED AS A PRECAUTION.  THE O-RING SEALS DID NOT APPEAR TO BE DAMAGED.  (K)                                                                                                                                         1L71 3O    NTA47CE                        
20061107000622006110700062GL  2006       11         7          2006FA0001053    120061010G2810C36L            CAP                                     DIAMONDA40  DA40        2990002GL                                                               WING FUEL TANK  LEAKING         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM07423FP38                     40FC023                                 UPON PREFLIGHT OF THE AIRCRAFT, AND AFTER SITTING OUTSIDE OF THE HANGAR DURING A RAINSTORM, 2 OR 3 SUMP GLASSES WERE FILLED WITH WATER FROM EACH WING FUEL TANK SUMP DRAIN.  FURTHER INSPECTION OF 9 OTHER AC OF THE SAME MAKE AND MODEL FOUND 2 OTHER AC WITH SIMILAR AMOUNTS OF WATER IN THE SUMP DRAINS.  ALL 3 OF THESE AC WERE TIED DOWN OUTSIDE DURING WEATHER ABOVE STATED.  INSPECTION OF THE FUEL FILLER FLANGE/CAP ASSY ON ALL 12 AC REVEALED THE SAME LOOSE FUEL CAP CONDITION.  ALL AC FUEL CAPS WERE TIGHTENED AS A PRECAUTION.  THE O-RING SEALS DID NOT APPEAR TO BE DAMAGED.  (K)                                                                                                                                               1L71 3O    NTA47CE                        
20061107000632006110700063    2006       11         7          2006FA0001055    220061025G855083278           PRESSURE SWITCH                         CESSNA172   172R        2072401CE                                                               ENGINE OIL      LEAKING         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE01243522618                   17280835                                AC WAS MAKING AN APPROACH AND HAD OIL SPLASH ON THE WINDSHIELD.  PILOT MADE A FULL STOP AND TAXIED BACK TO RAMP.  OIL PRESSURE AND TEMPERATURE STAYED IN THE GREEN.  UPON INVESTIGATION, FOUND THE CAUSE OF THE OIL LEAK TO BE THE (SENSOR-OIL PRESSURE (HOBBS-SWITCH) PN 83278 TO BE THE SOURCE OF THE LEAK.  THE SENSOR HAD FAILED INTERNALLY AND THE OIL WAS COMING FROM AROUND THE PRONGS INSIDE THE CONNECTOR AREA.  PROBABLE CAUSE-BAD DESIGN.  PREVENT REOCCURRENCES-UNKNOWN.  (K)                                                                                                                                                                                                                                                       1H71 3O    NT3A12                         
20070605002132007060500213CE  2007       6          5          2006FA0001056    120061022G5100                PIN                                     CESSNA182   R182        2072734CE  LYC   O540  O540*       41532EA                              ACTUATOR        BROKEN          B      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE015274S                       R18201534                               LOCKDOWN PINS BROKE AT GROOVE FOR ROLL PINS.  THIS ALLOWED THE PINS TO MOVE OUT OF ACTUATOR BEARING END AND JAM THE ACTUATOR.  IN THE UNLOCKED POSITION, SEB95-20 ACTUATOR DOWNLOCK PIN.  INSPECTION SAYS TO CHECK FOR LOOSE PINS.  THESE PINS WERE NOT LOOSE IN THE END BEARING UNTIL THE PART WAS THOROUGHLY CLEANED.  THERE ARE INDICATIONS THAT THE PINS WERE MOVING BUT COULD NOT BE MOVED.   THE NEW ASSEMBLIES USE A PIN THROUGH THE PINS INSTEAD OF A GROVE CUT IN THE CIRCUMFERENCE OF THE LOCKDOWN PIN.  SUGGEST THAT ANY ACTUATORS THAT ARE STILL OUT THERE BE REMOVED AND CLEANED TO DETERMINE  THAT THE PINS ARE BROKEN OR LOOSE.  (K)                                                                                             1H71 3O3  ORT3A13    E295                 
20061205002962006120500296SO  2006       12         5          2006FA0001057    120061025G78301159SCP40211RW  ACTUATOR                                GULSTMG1159 GIV         3980115SO  RROYCETAY   TAY6118          EU                              THRUST REVERSER FAILED          D      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            NRNOT REPORTED   1                      WP01595PE143  143               1373        16871                       APPROXIMATELY 20 MINUTES INTO THE FLIGHT, THE CREW NOTIFIED MAINTENANCE THAT THEY HAD A (T/R REV UNLOCK) LIGHT.  THE CREW BROUGHT BACK POWER AND THE LIGHT EXTINGUISHED, CREW THEN SELECTED (EMERGENCY STOW) AND RETURNED TO DEPARTURE WITHOUT INCIDENT.  AS THE AIRCRAFT ROLLED UP WITH ENGINES RUNNING, MAINTENANCE NOTED THE LT T/R DROOPED APPROX .1250 INCH, BUT STILL NOT ON THE SECONDARY LOCK (S HOOKS).  THIS ACTUATOR HAD BEEN INSTALLED IN FEB 2006.  A NEW REPLACEMENT ACTUATOR PN: 1159CP402-11, SN 2268 HAS BEEN INSTALLED WITH NO FAULTS NOTED AND THE AC HAS BEEN RETURNED TO SERVICE.  (K)                                                                                                                                     2L72 4F4  FRTA12EA   E25NE                
20061117001662006111700166CE  2006       11         17         2006FA0001058    120061018G34110800106379      PITOT LINE                              CESSNA310   T310Q       2074244CE  CONT  O520  TSIO520*    17040SO                                              CORRODED        D      K   NONE                                                                                            L  NO TEST                                                                       ININSP/MAINT     1                      WP1787JV                        310Q0206                                DURING A ROUTINE PITOT/STATIC TEST, FOUND THAT THE PITOT SYSTEM WAS LEAKING BEYOND LIMITS.  THE LEAKAGE WAS DETERMINED TO BE IN THE TUBING FROM THE PITOT TUBE TO THE FORWARD CABIN BULKHEAD FITTING.  UPON REMOVING THE TUBE (PN 0800106-379) SEVERE CORROSION WAS FOUND AT THE AFT  END, NEAR THE FITTING.  THIS PORTION WAS FOUND HALF BURIED IN THE OUTER INSULATION OF A HEAT DUCT ON THE LT OB SIDE, ALLOWING MOISTURE TO BE TRAPPED.  THIS AREA IS DIFFICULT TO INSPECT AND DAMAGE TO THE TUBE COULD GO UNDISCOVERED UNTIL A LEAK TEST IS PERFORMED.  IT IS RECOMMENDED THAT OPERATORS OF AC HAVE THIS LINE INSPECTED, AND THAT CHAFE AND CORROSION PROTECTION BE APPLIED TO THE TUBE WHERE IT CONTACTS THE INSULATION OF THE HEAT DUCT. 1L72 3O3  O  3A10    E8CE                 
20061205003092006120500309EA  2006       12         5          2006FA0001059    220061020G852072877           LIFTER                                  PIPER PA32  PA32300     7103212SO  LYC   O540  IO540K1A5   41532EA                              ENGINE          BROKEN          B  JUJRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO071102N     1800              3240756     L1236848                    LIFTER BROKE. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L71 3O3  O  A3SO    1E4                  
20061205003102006120500310EA  2006       12         5          2006FA0001060    220061020G852072877           LIFTER                                  CESSNA182   182S        2072701CE  LYC   O540  IO540AB1A5       EA                              ENGINE          BROKEN          B  JUJRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO079581V1138                   18280257    L2639348A                   LIFTER BROKE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O3  ONT3A13    1E4                  
20061205003112006120500311EA  2006       12         5          2006FA0001061    220061020G8520AEL72877        LIFTER                                  PIPER PA46  PA46350P    7104602SO  LYC   O540  TIO540AE2A  41532EA                              ENGINE          BROKEN          B  JUJRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO07146DG1400                   4636066     L975261A                    LIFTER BROKE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L71 3O3  ORTA25SO   E14EA                
20061205003122006120500312EA  2006       12         5          2006FA0001062    220061003G85201382712170      CRANKSHAFT                              CESSNA172   172R        2072401CE  LYC   IO360 IO360L2A         EA                              ENGINE          CORRODED        B  YYBRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL03987WU2216                   17280550    L170551A                    INSIDE DIAMETER WAS FOUND TO BE PITTED AFTER REMOVAL OF THE COATING CALLED URETHABOND 104.  THIS COATING WAS APPLIED BY MFG.  THE SURFACE APPEARED TO BE VERY ROUGH, ALMOST THREADED.  THE CAUSE FOR THE CORROSION IS UNCERTAIN.  A SUGGESTION FOR PREVENTION IS NOT POSSIBLE.  MY SPECULATION WOULD BE THAT THE COATING IS NOT ADEQUATELY SEALING THE SURFACE FROM MOISTURE.  (K)                                                                                                                                                                                                                                                                                                                                                              1H71 3O3  ONT3A12    1E10                 
20061205003152006120500315CE  2006       12         5          2006FA0001063    120061011G8011PM2401          STARTER                                 CESSNA172   172S        2072439CE                                                               ENGINE          FAILED          D      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      NM01686SP                       172S8097                                BENDIX GEAR FAILS DURING START OPERATION.  INSTALLED ON 3/10/04, REMOVED ON 8/16/04.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3O    NT3A12                         
20061205003162006120500316EA  2006       12         5          2006FA0001064    220061012G853017F19357        ROCKER                                  ROBSINR22   R22BETA     7640110NM  LYC   O360  O360J2A     41514EA                              NR 4 CYLINDER   CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP17776SH     5                 3552                                    NR 4 CYLINDER INTAKE ROCKER ARM CRACKED/SPLIT INTO 2 PIECES.  CRACK/ SPLIT RUNS CROSS-WAYS NEAR ROCKER BOSS ON VALVE STEM SIDE OF ROCKER ARM.  AGGRESSIVE MACHINING OF ROCKER ARM AND OR ROCKER ARM INCORRECTLY CONTACTING KEEPER SPRING ASSEMBLY.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1G71 3O3  O  H10WE   E286                 
20070118000302007011800030    2007       1          18         2006FA0001065    420060918G256446FASA631201    LIFE RAFT                                                                                                                               CABIN           PARTIAL INFLATE D  WV1RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO35                                                                    LIFE RAFT PARTIALLY INADVERTENTLY DEPLOYED IN CUSTOMERS AIRCRAFT CABIN AREA (UNDER SEAT CUSHION) WHICH COULD HAVE POSSIBLY CAUSED SEVERE DAMAGE TO THE AIRCRAFT, INJURY TO PERSONS OR LOSS OF AIRCRAFT CONTROL HAD LIFE RAFT COMPLETELY INFLATED IN-FLIGHT.  THE LIFE RAFT WAS REMOVED FROM THE AIRCRAFT CABIN BY THE OPERATOR BEFORE IT HAD COMPLETELY INFLATED MINIMIZING THE POSSIBILITY OF SEVERE DAMAGE.  (K)                                                                                                                                                                                                                                                                                                                                                                        
20061115003102006111500310    2006       11         15         2006FA0001066    420060926G256446FASA2303603   LIFE RAFT                                                                                                                               CABIN           PARTIAL INFLATE C  WV1RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO35                                                                    LIFE RAFT PARTIALLY INADVERTENTLY INFLATED IN CUSTOMERS AIRCRAFT CABIN AREA (UNDER SEAT CUSHION) WHICH COULD HAVE POSSIBLY CAUSED SEVERE DAMAGE TO THE AIRCRAFT, INJURY TO PERSONS OR LOSS OF AIRCRAFT CONTROL HAD LIFE RAFT COMPLETELY INFLATED IN-FLIGHT.  THE LIFE RAFT WAS REMOVED FROM THE AIRCRAFT CABIN BY THE OPERATOR BEFORE IT HAD COMPLETELY INFLATED MINIMIZING THE POSSIBILITY OF SEVERE DAMAGE.  (K)                                                                                                                                                                                                                                                                                                                                                                        
20061205003172006120500317EA  2006       12         5          2006FA0001067    220060926G8530SI74673         COMPRESSION RING                        GULSTMG44   G44         3951502SO  LYC   O480  GO480B1C    41527EA                              PISTON          IMPROPER        D  AV2RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW15645DH                       1329        L29228                      SUPERIOR COMPRESSION RINGS PN 74673 WERE INSTALLED DURING OVERHAUL, AFTER 3.0 HRS OF RUNNING A BORE SCOPE INSPECTION REVEALED SOME STRANGE BLACKENING OF THE CYLINDER WALLS.  A CYLINDER WAS REMOVED TO INVESTIGATE AND THE TOP (2) COMPRESSION RINGS ONLY SHOWED CONTACT ON THE BOTTOM HALF INDICATING THAT THE BEVEL ON THE FACE OF THE RING WAS FACING THE WRONG WAY FOR A COMPRESSION RING.  AFTER COMPARING THIS SUPERIOR RING TO A MFG RING IT APPEARS THE SUPERIOR RING IS DEFECTIVE, NUMBERED WRONG, BUT DOES NOT MATCH THE SHAPE OF THE RING AND INFORMATION OBTAINED FROM MFG TECH SUPPORT.  SUBSEQUENTLY ALL CYLINDER HAVE BEEN REMOVE TO REPLACE THESE RINGS.  RECOMMEND THAT ALL RINGS FROM MFG BE RECALLED FROM THE SYSTEM FOR SAF1H72 3I3  OO A734    E275                 
20061115003062006111500306SO  2006       11         15         2006FA0001068    120061103G792120017A          OIL COOLER                              PIPER PA28  PA28R201    7102816SO  LYC   O360  IO360C1C6   41514EA                                              LEAKING         B      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CLCLIMB          1                      GL21287ND2365 3                 2844036     L1731751A                   PILOT REPORTED FLICKERING OIL PRESSURE ANNUCIATOR DURING TAKE-OFF. LANDED AND FOUND OIL LEAKING FROM OIL COOLER AREA. UPON CLOSER EXAMINATION BY A&P DETERMINED COOLER WAS LEAKING IN BETWEEN THE COOLING FINS. COOLER WAS REPLACED RUN UP AND LEAK CHECKED GOOD. OIL LEVEL NEVER EXCEDED MINIMUM QUANTITY.                                                                                                                                                                                                                                                                                                                                                                                                                                     1L71 3O3  O  2A13    1E10                 
20061115003302006111500330EA  2006       11         15         2006FA0001069    220061109G8530LW19001         EXHAUST VALVE                           CESSNA182   182S        2072701CE  LYC   O540  IO540AB1A5       EA  MCAULY3D36C B3D36C431   GL  ENGINE CYLINDER STUCK           B  JRURK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL07715HP501                    18280921    RL2126148A  060202          STUCK EXHAUST VALVES ON NR 3 CYLINDER FOUND DURING PHASE 2 INSPECTION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3O3  ONT3A13    1E4     5  C         
20061205003182006120500318CE  2006       12         5          2006FA0001070    120060223G8011646275          BEARING                                 CESSNA210   T210N       2073456CE  CONT  O520  TSIO520R    17040SO                              STARTER MOTOR   SEIZED          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO156622N                       21063125                                OVERHAULER W/O NR 84062, O/H DATE 10/06/2006.  STARTER BEARING SEIZED AFTER INSTALLATION STARTER MOTOR FAILED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3O3  O  3A21    E8CE                 
20061205003192006120500319CE  2006       12         5          2006FA0001071    120061028G57201011200953      WEB                                     BEECH 200   B200        1152922CE  PWA   PT6   PT6A42      52043NE                              LT WING         CRACKED         B  B92RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE07828FM                       BB1069                                  DURING PHASE 1 THROUGH 4 INSPECTION, AFTER REMOVING MOVING ALL WING INSPECTION PANELS.  4 (EA) CRACKS NOTICED IN WEB FLANGE COMMON TO AND EMITTING FROM RIVETS ON LT IB WING BOX AREA, BL-65.50, (2EA) CRACKS AT WS 65, (1EA) CRACK AT WS 56.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L72 4T4  T  A24CE   E4EA                 
20061117000492006111700049SO  2006       11         17         2006FA0001072    120060904G27106271605         SHAFT                                   PIPER PA32  PA32300     7103212SO  LYC   O540  TIO540*     41532EA                              AILERONS        FAILED          C      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW154112R                       3240431                                 THE HOLE IN THE SHAFT WAS MISDRILLED WHERE THE TAPER PIN ATTACHES IT TO THE SPROCKET, WHICH IS PART OF THE AILERON CONTROL SYSTEM.  THE MISDRILLED HOLE ALLOWED THE PIN TO BREAK FREE OF THE SHAFT.  THIS FAILURE CAUSED THE SEPARATION OF THE RT CONTROL WHEEL FROM THE AIRPLANE FLIGHT CONTROL SYSTEM.  THIS PROBLEM WAS FOUND WHILE CONDUCTING OTHER MAINTENANCE ON THE AIRCRAFT.  THE PART IS AVAILABLE FOR INSPECTION.  PHOTOS OF THE PART ARE AVAILABLE VIA E-MAIL. (K)                                                                                                                                                                                                                                                                   1L71 3O3  O  A3SO    E14EA                
20061205003202006120500320CE  2006       12         5          2006FA0001073    120061029G322008424008        BRACKET                                 CESSNA182   182A        2072704CE  CONT  O470  O470*       17026SO                              NLG             FAILED          D      O   OTHER                                                                                           E  VIBRATION/BUFFET                                                              LDLANDING        1                      WP075166D5400                   51266                                   DURING LANDING ROLL OUT THE NOSE GEAR BEGAN TO SHIMMY UNTIL NOSE GEAR FAILURE.  AN INSPECTION SHOWN, A FAILURE OF THE NOSE GEAR SHIMMY DAMPER BRACKET ON HOUSING.  PART ORIGINAL TO 1958 INSTALLATION.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1H71 3O3  ONT3A13    E273                 
20061205002372006120500237SW  2006       12         5          2006FA0001074    120061031G3250350501          SERVO                                   SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE3313U    01514WP  HARTZLHCB3T HCB3TN5     GL  NLG STEERING    MALFUNCTIONED   G      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO17247ML                       TC247                                   AIRCRAFT PULLS TO THE RT.  OPERATOR REMOVED AND REPLACED NOSE STEERING SERVO, FLUSHED OUT LINES AND REPLACED FILTER.  OPS CHECK GOOD IAW MFG MM.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4T4  TRTA8SW    E4WE    6  CP15EA    
20061205003212006120500321CE  2006       12         5          2006FA0001075    120061011G8011PM2401H         STARTER                                 CESSNA172   172S        2072439CE  LYC   O360  IO360A1A    41514EA                              ENGINE          FAILED          D      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      NM01686SP177                    172S8097                                THE BENDIX GEAR CRACKED/SHATTERED DURING START OPERATION.  NO DAMAGE TO RING GEAR.  PART INSTALLED ON 6/23/2006.  PART REMOVED ON 10/11/2006.  THIS IS BECOMING A VERY BIG PROBLEM WITH THESE STARTERS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H71 3O3  ONT3A12    1E10                 
20070131002552007013100255    2007       1          31         2006FA0001076    220061030G8520                CONNECTING ROD                          AMTR  RWEXECROTORWAY162F       GL                                                               ENGINE          FAILED          G      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      SW11162HM                       6135                                    ENGINE FAILED ON CIRCLING CLIMB FROM AIRPORT.  ROD CAME THRU ENGINE BLOCK.  (INCIDENT ISW1107003) (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1G71 3O      EXPA1G71                     
20061205002592006120500259SO  2006       12         5          2006FA0001077    220060928G8530SA10200A1       CYLINDER                                CESSNA150   150M        2071830CE  CONT  O200  O200A       17020SO                              NR 3            CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NE05714DG1100                   15079092                                OIL LEAK LEAD TO FINDING CYLINDER BARREL CRACKED, MID SECTION IN COOLING FINS, .7500 WAY AROUND BARREL.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H71 3O3  O  3A19    E252                 
20070118000332007011800033SO  2007       1          18         2006FA0001078    120061031G321365489000        STRUT                                   PIPER PA28  PA28161     7102803SO  LYC   O320  O320D3G     41508EA  SNSNCH74D   74DM        EA  MLG             DEPARTED        B      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP095513V                       287716181   L802639A                    WHILE PRACTICING TAKEOFF AND LANDINGS, THE TOWER INFORMED PILOT THERE WAS A PROBLEM WITH LEFT LANDING GEAR.  THE INSTRUCTOR ELECTED TO RETURN TO TAKEOFF AIRPORT.  UPON LANDING THE BRAKEHOSE SEPARATED, AND THE WHEEL, BRAKE ASSY, STUB AXEL AND OLEO PISTON DEPARTED WHEN LANDING WAS MADE ON BOTTOM OF LT GEAR CYLINDER.  PROBABLE CAUSE IS NUMEROUS HARD LANDINGS WITH STUDENTS FLYING. (K)                                                                                                                                                                                                                                                                                                                                                 1L71 3O3  O  2A13    E274    5  NP88614   
20061205003222006120500322GL  2006       12         5          2006FA0001079    120061005G2434653344          ALTERNATOR                              CIRRUSSR    SR20        05628AJGL  CONT  O360  IO360ES          SO  HARTZLHCJ2Y BHCJ2YF1    GL  ENGINE          SEPARATED       D      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      NM01269CD940                    1204        357442      EF282B          DURING FLIGHT, PILOT NOTICED A LOUD BANGING NOISE FROM UNDER ENGINE COWLING PILOT PROCEEDED TO LAND.  AFTER LANDING, MAINTENANCE DEPARTMENT.  REMOVED COWLING TO FIND THIS ALTERNATOR SEPARATION/ FAILURE.  NO OTHER COMPONENTS WERE DAMAGED.  INSPECTION PRIOR TO THIS FAILURE SHOWED NO DEFECT TO THIS COMPONENT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                        1L71 3O3  ONTA00009CHE1CE    5  CP37EA    
20061212002882006121200288    2006       12         12         2006FA0001080    120061016G2750790231509       CONTROL VALVE                                                                                                                           T/E FLAP        DEFECTIVE       B  W6NRK   NONE                                                                                            F  FLT CONT AFFECTED                                                             ININSP/MAINT     1                      GL25                                                                    PART HAD OVERHAULED TAG INSTALLED SEPT 2004.  THE PART WAS INSTALLED ON A COMMANDER AND STILL HAD THE SAME PROBLEM OF DROOPING FLAPS.  WE SENT THE UNIT BACK AND THEY SAID IT NEEDED REPAIRED AND ADDITIONAL SERVICED PERFORMED.  THE UNIT WAS SENT BACK TO US JULY 2005 AND THE INSTALLED ON ANOTHER AIRCRAFT IN JULY 2006 AND THE SAME PROBLEM OCCURRED WE HAD ON THE PREVIOUS AC.  THIS UNIT WAS NOT ON THE AIRCRAFT LONG ENOUGH TO DO ANY KIND OF DAMAGE.  WE RAN THE FLAP SYSTEM 1 TIME AND STILL SAME PROBLEM.  WE SENT THE PART BACK AGAIN AND THEY SAID IT NEEDED OVERHAULED THIS TIME.  WE INSTALLED A NEW FLAP VALVE ON THE AIRCRAFT AND THE PROBLEM IS GONE.  (K)                                                                                                              
20070108001472007010800147SO  2007       1          8          2006FA0001081    120061101G25108994406         SEAT BACK                               PIPER PA46  PA46350P    7104602SO  LYC   O540  TIO540*     41532EA                              COCKPIT         CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE07812MB                       4636111                                 CREW SEAT BACK FRAME CROSS SUPPORT BREAKS AT WELDED JOINT ON EITHER SIDE AND OR BOTH.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L71 3O3  ORTA25SO   E14EA                
20070116000122007011600012EA  2007       1          16         2006FA0001082    220061108G722010991004933     TUBE                                    BEECH 90    C90A        1152911CE  PWA   PT6   PT6A21      52043EA                              INLET           CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE01200HV                       LJ1478                                  THE TUBES ARE CRACKING ALONG THE WELDS, WHICH CONNECT THEM TO THE INLET LIP ASSEMBLY.  REQUIRES REMOVAL OF INLET LIP ASSY AND REPAIR OF THE CRACKED WELDS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L72 3T4  TRT3A20    E4EA                 
20070118000562007011800056NM  2007       1          18         2006FA0001083    120061002G323065446924        HOUSING                                 BOEING737   737*               NM                                                               MLG VALVE       CRACKED         C  IU6RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM01                                                                    REF (211263/KS2) HOUSING CRACKED IN VALVE BORE. CYCLIC STRESS. REDESIGN HOUSING. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F    RTA16WE                        
20061117001382006111700138NM  2006       11         17         2006FA0001084    120061006G291365447822        HOUSING         BOEING                  BOEING737   737*               NM                                                               VALVE           ERODED          D  IU6RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM01                1795                                                (REF: 211704/QN1) PIN HOLE ERODED IN NR 2 PORT HEEL.  MATERIAL DEFECT/ TIME.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F    RTA16WE                        
20070109000062007010900006GL  2007       1          9          2006FA0001085    220061103G726023034787AL      BEARING         ALLSN                   HUGHES369   369D        4470706WP  ALLSN 250C  250C20B     03013GL                              GEARBOX         SPALLED         B  EOORO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      AL03CGPHC           CAG35789    180257D     CAE830015                   VISIBLE LINE FOUND ON 2.5 BEARING ROLLERS MATCHING SPALLING FOUND ON SAG SHAFT (SDR DATED 3/NOV/2006).  GEARBOX INSTALLED 6/SEPT/2006.  TIME IN SERVICE FOR GEAR BOX, 105.1 HOURS.  2.5 BEARING INSTALLATION TIMES NUT SHOWN ON ENGINE CARDS.  2.5 BEARING IS A PMA PART ALCOR.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                            1G71 3U3  U  H3WE    E4CE                 
20070108001722007010800172WP  2007       1          8          2006FA0001086    120061004G5300369A75058       SUPPORT                                 HUGHES369   369D        4470706WP  ALLSN 250C  250C20B     03013GL                              ANTITORQUE PEDALCORRODED        B  EOORO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      AL03511SB                       1090592D                                DURING ANNUAL INSPECTION PEDAL SUPPORT WAS FOUND WITH CORROSION ON LOWER BOLT PADS BEYOND REPAIRABLE LIMITS.  REPLACED SUPPORT BRACKET WITH SERVICEABLE PART.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1G71 3U3  U  H3WE    E4CE                 
20070116000542007011600054GL  2007       1          16         2006FA0001087    220061103G7230E23031922C      SHAFT           ALLSN                   HUGHES369   369D        4470706WP  ALLSN 250C  250C20B     03013GL                              COMPRESSOR ASSY SPALLED         B  EOORO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      AL03CGPHC           CAC362283   180257D     CAE830015                   FOUND SPALLING ON BEARING RACE AT 2.5 BEARING CONTACT POINT.  FOUND VISIBLE LINE ON 2.5 BEARING ROLLERS MATCCHING SPALL LINE ON SAG SHAFT.  COMPRESSOR ASSY INSTALLED ON AC 6/SEPT/2006, TIME IN SERVICE SINCE INSTALLATION OF COMPRESSOR ASSY 105.1 HOURS, 220 CYCLES.  INSTALLATION TIMES NOT SHOWN ON ENGINE CARDS FOR SAG SHAFT.  SAG SHAFT IS A PMA PART-EXTEX.  (K)                                                                                                                                                                                                                                                                                                                                                                       1G71 3U3  U  H3WE    E4CE                 
20070104000632007010400063SW  2007       1          4          2006FA0001088    120061119G62002040408123      ADAPTER                                 BELL  205   205A1       1181414SW  LYC   T53   T5313B      41549NE                              MAIN ROTOR      DAMAGED         B  EOORO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      AL03CGREU                       30011                                   DURING INSPECTION AND REGREASE OF THE M/R TRANS DRIVE SHAFT, A CHECK OF THE TORQUE OF THE DRIVE SHAFT ADAPTOR BOLT WAS ACCOMPLISHED AND IT WAS DISCOVERED THAT THERE WAS NO TORQUE, THAT THE BREAKER BAR`S WEIGHT BROKE THE BOLT LOOSE, REMOVED THE ADAPTOR AND FOUND WEAR ON THE ADAPTOR FLANGE AND IT WAS BEYOND LIMITS IAW TECH BULLETIN.  REPLACED PART.  (K)                                                                                                                                                                                                                                                                                                                                                                               1G71 4U4  U  H1SW    E17EA                
20061117001332006111700133CE  2006       11         17         2006FA0001089    120061115G5210MS203922C63     HINGE PIN                               BEECH 35    V35B        1151548CE                                                               CABIN DOOR      LOOSE           D      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      SO2566WC 2540                   D10199                                  CABIN DOOR TOP HINGE PIN KEEPER COTTER PIN FAILED. THE PIN, A CLEVIS BOLT, WAS INSTALLED FROM THE BOTTOM DUE TO STRUCTURAL DESIGN LIMITATIONS. THE FAILURE OF THE COTTER PIN ALLOWED THE CLEVIS PIN THE PARTIALLY FALL OUT OF PLACE ALLOWING THE DOOR TO MOVE. COMPLETE LOSS OF THE PIN MIGHT HAVE ALLOWED THE DOOR TO SEPARATE FROM THE AIRCRAFT IN FLIGHT. POSSIBLE IMPACT WITH THE RT RUDDERVATOR. CLOSER INSPECTION AT ANNUAL AND INSTALLING THE PIN FROM THE TOP WOULD HELP AVOID THE PROBLEM.                                                                                                                                                                                                                                             1L71 3O      3A15                         
20061117001342006111700134EA  2006       11         17         2006FA0001090    220061115G74146393            MAGNETO                                 PIPER PA23  PA23250     7102308SO  LYC   O540  IO540C4B5   41532EA                              ENGINE          FAILED          D      O   OTHER                                                                                           RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  TXTAXI/GRND HDL  1                      GL1315FG 630  140               277554112   L1313448A                   PILOT REPORTED THAT HE STARTED LT ENGINE AND THEN ATTEMPTED TO START RT ENGINE ON THE GROUND.  RT ENGINE WOULD NOT FIRE.  TROUBLESHOT AND TRACED PROBLEM TO LT MAGNETO OF RT ENGINE.  REMOVED LT MAGNETO FROM ENGINE.  UPON REMOVAL, LOOSE PARTS COULD BE HEARD INSIDE OF MAGNETO.  MAGNETO WAS DISASSEMBLED.  THE WEDGES HOLDING THE COIL IN PLACE WERE FOUND TO BE DISLODGED AND THE COIL HAD SHIFTED AND TAB WAS NOT MAKING CONTACT WITH DISTRIBUTOR BRUSH.  MAGNETO WAS INSPECTED AND ALL OTHER PARTS WERE FOUND TO BE SERVICEABLE.  A NEW COIL AND WEDGES WERE INSTALLED AND THE MAGNETO WAS REINSTALLED ON THE ENGINE AND OPERATED SATISFACTORILY.  THIS MAGNETO WAS NEW AT ENGINE INSTALLATION 630 HOURS AGO AND HAD BEEN DISASSEMBLED AN1L72 3O3  O  1A10    1E4                  
20061117001372006111700137CE  2006       11         17         2006FA0001093    120061115G5210MS203922C63     HINGE PIN                               BEECH 35    V35B        1151548CE  CONT  O520  IO520*      17032SO                              CABIN DOOR      LOOSE           D      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      SO2566WC 2540                   D10199                                  CABIN DOOR TOP HINGE PIN KEEPER COTTER PIN FAILED. THE PIN, A CLEVIS BOLT, WAS INSTALLED FROM THE BOTTOM DUE TO STRUCTURAL DESIGN LIMITATIONS. THE FAILURE OF THE COTTER PIN ALLOWED THE CLEVIS PIN THE PARTIALLY FALL OUT OF PLACE ALLOWING THE DOOR TO MOVE. COMPLETE LOSS OF THE PIN MIGHT HAVE ALLOWED THE DOOR TO SEPARATE FROM THE AIRCRAFT IN FLIGHT. POSSIBLE IMPACT WITH THE RT RUDDERVATOR. CLOSER INSPECTION AT ANNUAL AND INSTALLING THE PIN FROM THE TOP WOULD HELP AVOID THE PROBLEM.                                                                                                                                                                                                                                             1L71 3O3  O  3A15    E5CE                 
20061129003762006112900376EA  2006       11         29         2006FA0001094    220061116G7414M3548           ROTOR           SLICK                   PIPER PA28  PA28161     7102803SO  LYC   O320  O320D3G     41508EA  SNSNCH74D   74DM        EA  MAGNETO         SHEARED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW99     549        04081167                                            RT MAGNETO ROTOR SHEARED DIRECTLY UNDER THE PLASTIC ROTOR GEAR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L71 3O3  O  2A13    E274    5  NP88614   
20061204001062006120400106EA  2006       12         4          2006FA0001095    220061116G7314M3548           ROTOR           SLICK                   PIPER PA28  PA28161     7102803SO  LYC   O320  O320D3G     41508EA  SNSNCH74D   74DM        EA  MAGNETO         SHEARED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW99     549        04081167                                            RT MAGNETO ROTOR SHEARED DIRECTLY UNDER THE PLASTIC ROTOR GEAR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L71 3O3  O  2A13    E274    5  NP88614   
20061205002512006120500251SO  2006       12         5          2006FA0001096    120061106G7120102460036       MOUNT                                   PIPER PA46  PA46500TP   7104622SO  PWA   PT6   PT6*        52043EA                              ENGINE          CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM075215U757                    4697068                                 CUSTOMER REPORTED THAT HYDRAULIC PUMP KENP CYCLING.  INSPECTED LANDING GEAR ACTUATORS FOR LEAKS.  FOUND NLG ACTUATOR ATTACH CRACKED ON ENGINE MOUNT.  INSTALLING NEW ENGINE MOUNT IAW SB 1154A WILL SOLVE MALFUNCTION. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L71 3O3  TRTA25SO   E2NE                 
20061205002462006120500246CE  2006       12         5          2006FA0001097    120060815G32502609            SPRING                                  BBAVIA11    11AC        0191102CE  CONT  A65   A65*        17003SO                              TAIL STEERING   DAMAGED         G      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL153799E                       11ACS18                                 TAIL WHEEL SPRING STRETCHED AT HOOK CPVSWG PILOT TO LOOSE RUDDER CONTROL PAD DEPART TAXIWAY.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1H71 3O3  O  A761    E205                 
20061205002492006120500249CE  2006       12         5          2006FA0001098    120061107G2820LW120981116     PRIMER LINE                             CESSNA172   172N        2072434CE  LYC   O320  O320*       41508EA                              NR 3 CYLINDER   LEAKING         D      O   OTHER                                                                                           K  FLUID LOSS                                                                    TXTAXI/GRND HDL  1                      EA232059E                       17271137                                NOTED FUEL SPRAYING OUT WHEN TRYING TO PRIME ENGINE FOR START.  FOUND LINE CRACKING AT WELDED TIP AREA.  ON PRIMER LINE, WHERE IT ATTACHES TO CYLINDER FITTING.  THIS IS A BAD TYPE END ON LINE.  SUGGEST MORE SECURITY OF PRIMER LINES AT MORE PLACES, TO MINIMIZE VIBRATIONS. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3O3  ONT3A12    E274                 
20061205002392006120500239CE  2006       12         5          2006FA0001099    120061107G2497                WIRE                                    CESSNA172   172N        2072434CE  LYC   O320  O320*       41508EA                              ALTERNATOR      BROKEN          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA232059E                       17271137                                ALTERNATOR FAILED AND MAIN POWER BUS FEED WIRE BROKEN FROM ALTERNATOR.  TERMINAL ENDS, PROBABLY DUE TO VERY TIGHT AREA AND VIBRATION.  PREVENTION MIGHT BE TO ENLARGE AREA WHERE WIRES PASS THRU BAFFLING TO LIGHTEN VIBRATION AND STRESS ON WIRES BEING BENT TO FIT IN THIS AREA.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                         1H71 3O3  ONT3A12    E274                 
20070111001432007011100143CE  2007       1          11         2006FA0001100    120061025G2810128920185609    FUEL TANK                               BEECH MU300 400A        1155402CE                                                               AUX             DEBONDED        B  E81RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL0345RK 5423                   RK43                                    INVESTIGATED REPORTS OF IN-FLIGHT POPPING NOISES FROM UNDER FLOOR AREA ADJACENT TO CABIN DOOR.  FOUND FORWARD LT AUXILLARY TANK STRUCTURE UNDERSIDE HONEYCOMB PANELS DISBONDED FROM TANK STRUCTURE SHEETMETAL.  NO CORROSION NOTED, HONEYCOMB MATERIAL APPEARS TO HAVE SEPARATED FROM SHEETMETAL AT ADHESIVE BOND LINE.  SLIGHT DEFORMATION OF CURVED UNDERSIDE OF FUEL TANK STRUCTURE NOTED.  INFORMATION FORWARDED TO MFG FOR FOLLOW-UP INVESTIGATION.  POSSIBLE CAUSE IS VACUUM IN FUEL TANK DUE TO VENTING PROBLEM CAUSING TANK DEFORMATION AND/OR HONEYCOMB ADHESIVE FAILURE.  (K)                                                                                                                                                         2H72 4F    RTA16SW                        
20070112000012007011200001NE  2007       1          12         2006FA0001101    220061108G73210164248850      FUEL CONTROL                            SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1        NE                              ENGINE          MALFUNCTIONED   D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO15680CH2352                   3540        9798                        (4TH FLIGHT OF THE NIGHT) AFTER START UP, ALL SYSTEMS NORMAL, UPON LIFT OFF THE TURBINE AND ROTOR RPM SIMULTANEOUSLY DECREASED.  PILOT REDUCED PITCH AND LANDED ON PAD WITHOUT INCIDENT RPM RETURNED TO 100 PERCENT.  PILOT AND COPILOT CROSS CHECKED INSTRUMENTS AND CONTROLS POSITIONS, FOUND NORMAL.  A SECOND ATTEMPT WAS MADE WITH THE SAME RESULTS.  BOTH NEEDLES STAYED TOGETHER DURING EACH EVENT.  THE TURBINE AND ROTOR SPEED RETURNED TOT HE NORMAL RANGE UPON THE COLLECTIVE BEING RETURNED TO THE LOCKED POSITION.  AIRCRAFT WAS REMOVED FROM SERVICE.  MAINTENANCE PERFORMED VISUAL INSPECTIONS AND GROUND/FLIGHT OPERATIONAL CHECKS AND FOUND NO DEFECTS COULD NOT DUPLICATE.  MFC/GOV RETURNED TO MFG FOR EVALUATION.  (K)      1G71 3U3  U  H9EU    E19EU                
20070109000622007010900062NM  2007       1          9          2006FA0001102    120060904G575469738243        BOLT                                    BOEING737   737322      1384676NM  CFMINTCFM56 CFM563C1    13802EU                              SLAT TRACK      LOOSE           C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA35354UA                       24360                                   (REF NR: ATC0712) DURING AN A-CHECK INSPECTION OF RT WING LEADING EDGES.  THE OB TRACK ATTACHMENT BOLT ON THE NR 6 SLAT WAS FOUND TO BE LOOSE AND ALSO THE SPLIT PIN WAS MISSING.  A NON ROUTINE CARD, WO 3956/06 HAS BEEN RAISED TO FIT THE SPLIT PIN AND RECTIFY THE DEFECT.  A CONFIDENCE CHECK HAS BEEN CARRIED OUT ACROSS ALL THE LEADING EDGE ATTACHMENTS FOR THE FLAP TRACKS.  IN ADDITION ALL FLYING CONTROLS AND TRAILING EDGE FLAPS HAVE BEEN INSPECTED FOR CORRECT LOCKING AND FITMENT.  NO OTHER LOCKING OR ASSY DEFECTS WERE FOUND.  (K)                                                                                                                                                                                           2L72 4F4  FRTA16WE   E21EU                
20070108000042007010800004    2007       1          8          2006FA0001104    120061016G324250030967        BRAKE ASSY                                                                                                                              LANDING GEAR    MISREPAIRED     C  BIERK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA21                                                                    SPACER TUBES (PN 5012942) WERE MISSING FROM ASSEMBLY.  INCORRECT RETURN PINS WERE INSTALLED.  SHOULD BE PN 5001421, INSTALLED WERE PN 9535044.  SWAGE ADJUSTER ASSEMBLIES WERE INCORRECTLY SET FOR THIS SERIES OF BRAKE.  THE SWAGES WERE SET AT A DEPTH OF 0.18 INCH BELOW FLUSH, THEY SHOULD HAVE BEEN SET FLUSH WITH THE TOP OF THE ADJUSTER TUBE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                
20070108000072007010800007    2007       1          8          2006FA0001105    120061016G324250030967        BRAKE ASSY                                                                                                                              LANDING GEAR    MISREPAIRED     B  BIERK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA21                                                                    SPACER TUBES (PN 5012942) WERE MISSING FROM ASSEMBLY.  INCORRECT RETURN PINS WERE INSTALLED.  SHOULD BE PN 5001421, INSTALLED WERE PN 9535044.  SWAGE ADJUSTER ASSEMLIES WERE INCORRECTLY SET FOR THIS SERIES OF BRAKE.  THE SWAGES WERE SET AT A DEPTH OF 0.18 INCH BELOW FLUSH, THEY SHOULD HAVE BEEN SET FLUSH WITH THE TOP OF THE ADJUSTER TUBE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                 
20070108000022007010800002    2007       1          8          2006FA0001106    120061016G324250030967        BRAKE ASSY                                                                                                                              LANDING GEAR    MISREPAIRED     B  BIERK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA21                                                                    SPACER TUBES (PN 5012942) WERE MISSING FROM ASSEMBLY.  INCORRECT RETURN PINS WERE INSTALLED.  SHOULD BE PN 5001421, INSTALLED WERE PN 9535044.  SWAGE ADJUSTER ASSEMBLIES WERE INCORRECTLY SET FOR THIS SERIES OF BRAKE.  THE SWAGES WERE SET AT A DEPTH OF 0.18 INCH BELOW FLUSH, THEY SHOULD HAVE BEEN SET FLUSH WITH THE TOP OF THE ADJUSTER TUBE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                
20070108000032007010800003    2007       1          8          2006FA0001107    120061016G324250030964        BRAKE ASSY                                                                                                                              LANDING GEAR    MISREPAIRED     B  BIERK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA21                                                                    UPON CONDUCTING REPAIR TO REPLACE THE MISSING RETURN SPRING ASSEMBLY.  FOUND THAT THE SPACER TUBES (PN 5012941) WERE MISSING FROM THE REMAINING 3 RETURN SPRING ASSEMBLIES.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          
20070108000012007010800001    2007       1          8          2006FA0001109    120061016G324250030967        BRAKE ASSY                                                                                                                              LANDING GEAR    MISREPAIRED     B  BIERK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA21                                                                    SPACER TUBES (PN 5012942) WERE MISSING FROM ASSEMBLY.  INCORRECT PRESSURE PLATE INSTALLED ON BRAKE ASSY.  SHOULD PN 5006890, INSTALLED WAS PN 5005117.  PN 5006890 MEASURES .240 INCH THICK, PN 5005117 MEASURES .210 INCH THICK.  INCORRECT WEAR PAD WAS INSTALLED ON PRESSURE PLATE.  SHOULD BE PN 5007328, INSTALLED WAS 5005119. YOU CAN TELL THE DIFFERENCE BECAUSE PN 5007328 DOES NOT HAVE A MILLED OUT AREA FOR STRUT CLEARANCE.  INCORRECT STATIONARY DISK INSTALLED ON BRAKE ASSY.  SHOULD BE PN 5006892, INSTALLED WAS PN 9544028.  PN 5006892 MEASURES .240 INCH THICK, PN 9544028 MEASURES .210 INCH THICK.  INCORRECT INSULATORS WERE INSTALLED IN PISTONS.  SHOULD BE PN 50068951.  (K)                                                                                    
20070116000702007011600070WP  2007       1          16         2006FA0001110    220060907G725030607881        BLADE                                   RAYTHNDH125 HAWKER800XP 7150012CE  GARRTTTFE731TFE7315BR        WP                              LPT3            DAMAGED         B      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP07800WW                       258661      107869                      THE INFLIGHT SHUTDOWN OCCURED ON SEPT 7, 2006, AFTER LEVELING OFF AT 30,000 FT THE CREW REPORTED A LOUD BANG FROM THE NR 2 ENGINE.  THE CREW SECURED THE ENGINE, DIVERTED AND LANDED WITHOUT INCIDENT.  VISUAL INSPECTION OF THE AC REVEALED DISPLACED MATERIAL ON THE AIRCRAFT NACELLE, DUCTING.  ENGINE EXHAUST DUCT AND TURBINE SECTION IN THE FORM OF A UNCONTAINED MALFUNCTION.  THE ENGINE WAS RETURNED TO MFG FOR DISASSEMBLY AND INSPECTION.  DISASSEMBLY FINDINGS REVEALED MATERIAL LOSS ON THE LPT3 WHEEL BLADES IN THE FORM OF MID SPAN BLADE FRACTURES.  (K)                                                                                                                                                                        2L72 4F4  FRTA3EU    E6WE                 
20070108002832007010800283CE  2007       1          8          2006FA0001111    120061121G7810227450          CLAMP                                   CESSNA421   421C        2076016CE  CONT  O520  GTSIO520N   17032SO                              TAIL PIPE       CRACKED         C      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE01     1371                   1249                                    PN 2274-50 (ALSO PN NH1000897-50) CLAMP HOLDING TAILPIPE TO THE TURBO CRACKED LENGTHWISE ALONG THE CIRCUMFERENCE OF THE CLAMP.  TOTAL LENGTH OF THE CRACK IS 3 INCHES.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L72 3O3  O  A7CE    E7CE                 
20061129001982006112900198SO  2006       11         29         2006FA0001112    120061126G32137873803         AXLE                                    PIPER PA28  PA28161     7102803SO  LYC   O320  O320D3G     41508EA  SNSNCH74D   74DMS       EA  LANDING GEAR    CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP092525Y14786                  288516075                               DURING A SCHEDULED 100 HOURS INSPECTION OF THE LANDING GEAR, THE MECHANIC FOUND A CRACK ON RT MAIN LANDING GEAR UPPER PART. IT IS SUSPECTED THE FATIGUE OR STRESS CORROSION CRACKING COULD BE THE CAUSE. ANOTHER REASON WHY MOST OF RT MAIN LANDING GEAR WERE FOUND CRACKED IS PROBABLY THE DIFFERENCE OF STRUCTURAL STRENGTH BETWEEN RT AND LT WING. RT WING IS SLIGHTLY STRONGER THAN LT WING BECAUSE IT HAS A (WING WALK PANEL) WHICH DOES NOT ALLOW TRANSFER ALL THE LOADS OCCURRING ON LANDINGS TO THE MAJOR MASS (ENGINE), THIS THEORY IS JUST A STRUCTURAL ANALYSIS BASE ON EXPERIENCE BUT IT NEED BE TESTED AND PROVED.                                                                                                                 1L71 3O3  O  2A13    E274    5  NP88614   
20070116000772007011600077WP  2007       1          16         2006FA0001118    220061116G7200                ENGINE                                                                     GARRTTATF3  ATF36       29002WP                                              FIRE            D      O   OTHER                                                                                           A  FLAME/FIRE                                                                    NRNOT REPORTED   1                      WP07                                        P21210C                     ENGINE FIRE DURING MAINTENANCE GROUND RUN ON 10/2/2006, PERFORMED TO DETERMINE THE CAUSE OF FLUCTUATING OIL PRESSURE.  PROBABLE CAUSE OF FIRE FOUND TO BE MISSING ROLL PIN FROM ATOMIZER, FUEL, INTEGRAL FLOW DIVIDER. MISSING PIN PERMITTED ATOMIZER SHROUD TO MOVE, DEFLECTING FUEL FLOW AWAY FROM COMBUSTION CHAMBER UPSTREAM IN THE ATOMIZER.  HOT GASSES FROM COMBUSTION CHAMBER WERE PERMITTED TO FLOW INTO THE CAVITY BETWEEN ATOMIZER AND ATOMIZER SHROUD CAUSING FUEL TO IGNITE IN THE ATOMIZER.  FIRE BURNED THROUGH FUEL ATOMIZER PILOT DIAMETER AND THROUGH THE COMBUSTOR CASE.  MISSING ROLL PIN LOCATION IN THE ENGINE ASSY IS FULLY CAPTURED BY FUEL ATOMIZER SLEEVE PN 3002830-1. NO EVIDENCE OF THE MISSING WAS FOUND DURING DI       4  F          E7WE                 
20061204000012006120400001    2006       12         4          2006FA0001119    220061020G74146324            MAGNETO                                                                                                                                 ENGINE          FAILED          B  PX2RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE07                                                                    MAGNETO IS DEAD.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     
20061212003152006121200315    2006       12         12         2006FA0001120    120061110G8011PM2401          STARTER                                                                                                                                 ENGINE          FAILED          B  PX2RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE07     151                                                            STARTER SPINS, BENDIX DOES NOT ENGAGE RING GEAR.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     
20061212003182006121200318    2006       12         12         2006FA0001121    120061110G8011ES6462382       STARTER                                                                                                                                 ENGINE          MALFUNCTIONED   B  PX2RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE07                                                                    STARTER WILL NOT DISENGAGE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          
20061212003162006121200316    2006       12         12         2006FA0001122    220061114G8530EC636122ST      CYLINDER                                                                                                                                ENGINE          MISMANUFACTURED B  PX2RK   NONE                                                                                            WK INADEQUATE Q C            FLUID LOSS                                          ININSP/MAINT     1                      CE07                                                                    INSTALLED CYLINDER ASSEMBLE ON NEWLY OVERHAULED ENGINE.  DISCOVERED OIL LEAKING AROUND CYLINDER BASE DURING TEST CELL RUN.  REMOVED CYLINDER AND DETERMINED THAT THE CYLINDER BASE IS NOT PROPERLY MACHINED.  THERE IS NO RADIUS AT THE AREA WHERE THE O-RING SEAL IS TO SEAT.  THIS DOES NOT ALLOW THE O-RING TO PROPERLY SEAL AGAINST THE CRANKCASE.  USED RADIUS GAUGES AND OTHER CYLINDERS TO COMPARE AND MAKE THE DETERMINATION THAT THERE WAS A PROBLEM WITH THE CYLINDER.  (K)                                                                                                                                                                                                                                                                                                     
20061212003142006121200314    2006       12         12         2006FA0001123    220061114G8530EC636122ST      CYLINDER                                                                                                                                ENGINE          MISMANUFACTURED B  PX2RK   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CE07                                                                    INSTALLED CYLINDER ASSEMBLY ON NEWLY OVERHAULED ENGINE.  DISCOVERED OIL LEAKING AROUND CYLINDER BASE DURING TEST CELL RUN.  REMOVED CYLINDER AND DETERMINED THAT THE CYLINDER BASE IS NOT PROPERLY MACHINED.  THERE IS NO RADIUS AT THE AREA WHERE THE O-RING SEAL IS TO SEAT.  THIS DOES NOT ALLOW THE O-RING TO PROPERLY SEAL AGAINST THE CRANKCASE.  USED RADIUS GAUGES AND OTHER CYLINDERS TO COMPARE AND MAKE THE DETERMINATION THAT THERE WAS A PROBLEM WITH THE CYLINDER.  (K)                                                                                                                                                                                                                                                                                                     
20061212003172006121200317    2006       12         12         2006FA0001124    220061114G8530EC636122ST      CYLINDER                                                                                                                                ENGINE          MISMANUFACTURED B  PX2RK   NONE                                                                                            WK INADEQUATE Q C            FLUID LOSS                                          ININSP/MAINT     1                      CE07                                                                    INSTALLED CYLINDER ASSEMBLY ON NEWLY OVERHAULED ENGINE.  DISCOVERED OIL LEAKING AROUND CYLINDER BASE DURING TEST CELL RUN.  REMOVED CYLINDER AND DETERMINED THAT THE CYLINDER BASE IS NOT PROPERLY MACHINED.  THERE IS NO RADIUS AT THE AREA WHERE THE O-RING SEAL IS TO SEAT.  THIS DOES NOT ALLOW THE O-RING TO PROPERLY SEAL AGAINST THE CRANKCASE.  USED RADIUS GAUGES AND OTHER CYLINDERS TO COMPARE AND MAKE THE DETERMINATION THAT THERE WAS A PROBLEM WITH THE CYLINDER.  (K)                                                                                                                                                                                                                                                                                                     
20070108001412007010800141NM  2007       1          8          2006FA0001125    120061101G2100                CONTROL UNIT                            PIPER PA60  PA60602P    7106015NM                                                               AUTOPILOT       MALFUNCTIONED   C      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA0364715                       608365003                               AC WAS ACQUIRED IN AN OVERHAULED CONDITION FROM AUTO PILOTS CENTRAL.  THIS UNIT WAS AN EXCHANGE UNIT WITH AN OVERHAUL DATE OF APPROX, JUNE 2004.  THE KI-256 WAS INSTALLED AND MARRIED TO THE EXISTING FACTORY INSTALLED AUTOPILOT SYS IAW INSTALLATION/ SYS MM.  AC WAS RETURNED TO SERVICE AFTER A SUCCESSFUL FLIGHT CHECK.  ALL AUTOPILOT/ FLIGHT DIRECTOR MODES WERE CHECKED.  SINCE THEN THIS FD/HORIZON HAS BEEN REMOVED AND RETURNED TO OVERHAULER NO LESS THAT 3 TIMES.  HORIZON HAS BEEN RESPONSIBLE FOR AN ABRUPT AND ERRATIC PURPOSE.  THIS UNIT HAS ALWAYS FAILED IN AUTOPILOT PITCH MODE.  EACH TIME OVERHAULER FINDS A NEW PROBLEM IN PITCH CIRCUITS.  THESE PROBLEMS ARE RELATED TO THE AUTOPILOT IN THE PITCH AXIS, BUT EACH TIM1M72 3O    RTA17WE                        
20061129002162006112900216NE  2006       11         29         2006FA0001126    220061128G7314378200          PUMP                                                                       PWA   JT8   JT8D15A     52051NE                              FUEL SYSTEM     DAMAGED         C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW99          5360                                                      UNIT RECEIVED ON 13 NOV 2006.  UNIT PROCESSED ON A REPAIR WORKSHOP IAW CUSTOMER REQUIREMENTS.  PUMP FAILED AS RECEIVED BENCH TEST FOR LOW FUEL FLOWS.  PUMP DISASSEMBLED IAW CMM REF 73-11-1 TO INVESTIGATE INCOMING TEST FINDINGS.  DISASSEMBLY OF FUEL PUMP REVEALED EXTENSIVE DAMAGE TO IMPELLER ASSY. PN 216916.  DAMAGE WAS CAUSED AS A RESULT OF QTY 2 NUTS ENTERING FUEL PUMP FROM AN UNKNOWN EXTERIOR SOURCE.                                                                                                                                                                                                                                                                                                                                  4  F          E2EA                 
20061129002742006112900274CE  2006       11         29         2006FA0001127    120061127G53446511695204      HINGE                                   CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              UNKNOWN         CORRODED        B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW191200N                       0494                                    AT INSPECTION THE HINGE WAS FOUND CORRODED AND THE PINS WORN PAST LIMITS. A FACTORY NEW HINGE ASSY WAS ORDERED AND INSTALLED. UPON COMPLETION OF THE WORK THE AIRCRAFT WAS PRESSURIZED AND THE HINGE ASSY WAS FOUND TO BE LEAKING. UPON CLOSER INSPECTION THE SKIN THAT ATTACHES TO THE HINGE WAS NOT SEALED. MFG WAS CONTACTED WITH THE REQUEST TO PAY FOR THE SEALANT AND MAGNESIUM RIVETS. WE WERE INFORMED THAT MFG WILL NOT PAY FOR THESE PARTS UNLESS WE RETURNED THE HINGE ASSY. DUE TO THE AMOUNT OF TIME TO INSTALL AND FIT THIS HINGE WE DECLINED. MFG NEEDS TO INSPECT MORE CLOSELY THERE PARTS OR BE ABLE TO WORK BETTER WITH THEIR CUSTOMERS.                                                                                      1L72 4F4  F  A22CE   E1NE                 
20070118000192007011800019CE  2007       1          18         2006FA0001128    120061108G302010991004933     TUBE                                    BEECH 90    C90         1152913CE                                                               DUCT            CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE0139FB                        LJ1165                                  THE LIP-ASSY IS CRACKED AROUND THE WELDS FOR THE INLET AND OUTLET TUBES.  REQUIRES REMOVAL OF INLET LIP ASSY AND REPAIR OF CRACKED WELDS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L72 3T      3A20                         
20070116000692007011600069EA  2007       1          16         2006FA0001129    220061114G8530MS139973        KEEPER                                  PIPER PA31  PA31350     7103110SO  LYC   O540  LTIO540J2BD 41533EA                              EXHAUST VALVE   BROKEN          C      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL13599871550                   317552081   L170168A                    FOUND VALVE KEEPER BROKEN ON ROUTINE VALVE INSPECTION IAW SB 388C.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L72 3O3  O  A20SO   E14EA                
20070118000772007011800077EA  2007       1          18         2006FA0001130    220061114G853072050           KEEPER                                  PIPER PA31  PA31350     7103110SO  LYC   O540  LTIO540J2BD 41533EA                              INTAKE VALVE    BROKEN          C      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL13599871550                   317552081   L170168A                    FOUND NR 6 CYLINDER VALVE KEEPER BROKEN ON ROUTINE VALVE INSPECTION IAW SB 388C.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L72 3O3  O  A20SO   E14EA                
20070116000782007011600078CE  2007       1          16         2006FA0001131    120061030G2720002524040       RUDDER PEDAL                            BEECH 36    A36         1151604CE                                                               RUDDER          LOOSE           B  AKGRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE05304E 1015                   E3433                                   UPON INVESTIGATING LOOSE RUDDER PEDALS, THE ASSEMBLY WAS DISASSEMBLED AND IT WAS NOTED THAT THE SHAFT HAD BEEN DOUBLE DRILLED WITH THE HOLES OVERLAPING.  THE AIRCRAFT WAS CERTIFICATED JANUARY 2002; THE AIRCRAFT NOW HAS 1015.4 HOURS, TIME IN SERVICE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L71 3O      3A15                         
20070104000222007010400022WP  2007       1          4          2006FA0001132    220061026G7200TPE3316         ENGINE                                  BEECH 100   B100        1152919CE  GARRTTTPE331TPE3316     01514WP  HARTZLHCB4T HCB4TN5     GL  RIGHT           FAILED          D  GSTRO   OTHER                                                                                           T  ENGINE CASE PENETRATION                                                       ININSP/MAINT     1                      SW1393WT 4839                   BE80        P27168      CDA3823         DURING GROUND RUN FRO A POSSIBLE GENERATOR PROBLEM.  WITH THE ENGINE AT FLIGHT IDLE AND SPEED LEVERS FORWARDTHE RT ENGINE HAD A UNCONTAINED ENGINE FAILURE.  2 PIECES OF THE ENGINE PENETRATED THE RT FUSELAGE SKIN ADJACENT TO THE CO PILOT POSITION.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L72 4T4  T  A14CE   E4WE    6  CP40EA    
20070118000752007011800075CE  2007       1          18         2006FA0001133    120061114G3230508100398       DRAG BRACE                              BEECH 90    C90         1152913CE  PWA   PT6   PT6*        52043EA                              MLG             MISMANUFACTURED B      O   OTHER                                                                                           W  INADEQUATE Q C                                                                NRNOT REPORTED   1                      SO14690GT268                    LJ1727                                  UPPER DRAG BRACE PN 50-8100398 RUBBED AGAINST THE LOWER DRAG BRACE PN 508100404 AT THE KNUCKLE.  THIS REMOVED ABOUT .0625 OF AN INCH OF METAL ABOUT .0625 OF AN INCH LONG ON THE TOP SIDE OF BOTH ENDS OF THE KNUCKLE.  THE CAUSE IS IMPROPER MACHINING OF THE PART AT MANUFACTURE.  PARTS AFFECTED MUST BE REPLACED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                      1L72 3T3  T  3A20    E2NE                 
20070116000522007011600052EA  2007       1          16         2006FA0001134    220061120G7322                FLOAT           FACET                   AMRGENAA5   AA5B        3960105SO  LYC   O360  O360*       41514EA                              CARBURETOR      DAMAGED         B  H5GRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA0745343400        75115812    AA5B1265                                ENGINE IDLE AND LOW POWER PERFORMANCE WAS ERRATIC.  UPON ENGINE SHUTDOWN FUEL WAS NOTED DRIPPING FROM CARB/INDUCTION AIRBOX.  CARB WAS DISASSEMBLED AND INSPECTED.  FOUND PLASTIC TO HAVE PARTIALLY BECOME UNBONDED FROM LOWER SECTION ALLOWING FUEL TO BEGIN LEAKING INTO ASSEMBLY.  AS THE FLOAT LOST ITS BOUYANCY IT COULD NO LONGER RESTRICT FUEL SOURCE.  POOR RUNNING ENGINE AND A FIRE HAZZARD WERE THE RESULTS.  RECOMMEND THE MFG PROCESS (BONDING) OF THE FLOAT BE IMPROVED.  IN THE MEANTIME, ALL FLOATS MFG IN THE SAME BATCH SHOULD BE REMOVED FROM SERVICE.  (K)                                                                                                                                                                  1L71 3O3  O  A16EA   E286                 
20070125003012007012500301NE  2007       1          25         2006FA0001135    120061006G6320SB21511         BEARING                                 SKRSKYS64   S64E        8142604NE  PWA   JFTD12JFTD12A4A   52047NE                              M/R GEARBOX     CRACKED         C  JYDRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM09247AC1085       A6011       60452                                   (REF NR:MDR06-090)   MAIN GEARBOX PN 6435-20400065, SN A6-011 WAS REMOVED DUE TO FINDINGS OF FERROUS METAL IN THE OIL SCREEN AND FILTER.  UPON DISASSEMBLY AND TEAR DOWN, THE SOURCE OF THE FERROUS METAL WAS DISCOVERED TO BE COMING FROM GHE SECOND STAGE INPUT ALIGNMENT BEARING PN SB 2151-1, SN EAC18170.  THE SB2151-1 BEARING CRACKED THROUGH THE ENTIRE INNER RACE AND CAUSED SUBSEQUENT CONTAMINATION OF THE MAIN GEARBOX, AND DAMAGE TO THE SECOND STAGE PINION PN 6435-20457-104, SN 333 ALIGNMENT BEARING JOURNAL.  THE CRACKED INNER RACE WAS SENT TO THE MFG.  PROBABLE CAUSE: UNKNOWN.  (K)                                                                                                                                      2G72 4U4  U  H4EA    E15EA                
20070118000762007011800076NE  2007       1          18         2006FA0001136    120061006G6520SB21541         BEARING                                 SKRSKYS64   S64F        8142610NE  PWA   JFTD12JFTD12A4A   52047NE                              GEARBOX         CRACKED         B  JYDRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM09229AC958        EAC19192    64018                                   (REF NR MDR06-089)  THE IGB CHIP DETECTOR INDICATED A CHIP LIGHT.  IGB WAS REMOVED AND THE INNER RACE WAS FOUND TO BE CRACKED THROUGH AND SPALLED.  PROBABLE CAUSE: UNKNOWN. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2G72 4U4  U  H6EA    E15EA                
20061212003992006121200399NE  2006       12         12         2006FA0001137    220061106G7250597602          TURBINE BLADES                          SKRSKYS64   S64E        8142604NE  PWA   JFTD12JFTD12A4A   52047NE                              NR 2 ENGINE     FRACTURED       B  JYDRO   OTHER                                                                                           E  VIBRATION/BUFFET                                                              NRNOT REPORTED   1                      NM09CFCRN2946                   64061                                   (REF NR: MDR06-092)  VIBRATION FELT BY CREW, UPON LANDING, MAINTENANCE PERSONNEL FOUND METAL PARTICLES IN NR 2 ENGINE EXHAUST.  UPON CLOSER EXAMINATION, A 2ND STAGE TURBINE BLADE WAS FOUND TO BE FRACTURED APPROXIMATELY 1 INCH FROM THE ROOT.  THE FRACTURED PIECE BROKE OFF AND CAUSED SOME ADDITIONAL DAMAGE TO THE 2ND STAGE TURBINE BLADES AND EXTENSIVE DAMAGE TO THE FREE TURBINE AS IT DEPARTED.  (K)                                                                                                                                                                                                                                                                                                                                 2G72 4U4  U  H4EA    E15EA                
20061212004002006121200400NM  2006       12         12         2006FA0001138    120061031G275065446321        HOUSING                                 BOEING737   737*               NM                                                               T/E FLAP        CRACKED         B  IU6RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM01     53778                                                          (REF NR: 212286/ FXS)  HOUSING CRACKED INSIDE THE (P) PORT.  CYCLIC STRESS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F    RTA16WE                        
20061212002682006121200268EU  2006       12         12         2006FA0001139    120061101G2497                WIRE                                    ISRAEL1124  1124A       4500103EU  GARRTTTFE731TFE731*     01518WP                              ENGINE          CHAFED          B  YLMRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP23794TK                       373                                     AIRCRAFT ARRIVED WITH INOPERATIVE STRATER-GENERATOR.  TROUBLESHOOTING REVEALED INOPERATIVE GENERATOR, FAILED GENERATOR CONTROL UNIT, AND FAILED CONTROL RELAY.  FURTHER TROUBLESHOOTING FOUND (A) AND (D) LEADS TO STARTER-GENERATOR AT ENGINE WIRING WAS BRITTLE AND HAD BARE SPOT CHAFFED TO ENGINE INLET MOUNTING STRUT.  THIS ISSUE SHOULD BE CONSIDERED FOR ALL GENERAL AVIATION AIRCRAFT, NOT JUST THIS MFG.  WE HAVE NOTED CONDITION ON SEVERAL AIRCRAFT.  THIS IS THE FIRST INCIDENT, HOWEVER, THAT HAD CHAFFING AND A CIRCUIT SHORT.  RECOMMEND INSPECTION AT NEXT ACCESS FOR ALL GENERAL AVIATION TURBOJET AIRCRAFT AS THIS WIRING IS LOCATED IN EXTREME ENVIRONMENTAL CONDITIONS, WITHIN THE ENGINE COWLING.  (K)                    2M72 4F4  F  A2SW    E6WE                 
20070118000942007011800094CE  2007       1          18         2006FA0001140    120061107G261224412886        FIRE LOOP                               BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE  HARTZLHCE4A HCE4A3I     NE  RT ENGINE       MALFUNCTIONED   D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL13534M                        UE333       PCEPS0246   HJ1616          ON 10/4/2006, AFTER DEPARTING, APPROXIMATELY 30 MINUTES INTO THE FIRST LEG OF THE DAYS TRIP, THE PILOT REPORTED GETTING A RT ENGINE FIRE INDICATION.  FOLLOWING PROCEDURE, THE PILOT PULLED THE T-HANDLE AND BLEW THE FIRE BOTTLE, SHUTTING DOWN THE ENGINE.  THE PILOT DIVERTED TO AIRPORT AND LANDED SAFELY.  THE PILOT STATED THAT HE HAD NOT NOTICED ANY UNUSUAL READINGS FROM ANY OF THE GAUGES.  A MAINTENANCE CREW WAS SENT TO INVESTIGATE AND FOUND THAT THERE WERE APPROXIMATELY 3 QUARTS OF OIL LEFT IN THE ENGINE.  IT WAS DECIDED TO PULL THE ENGINE AND SEND IT FOR TESTING.  IT WAS ASSUMED THAT AN OIL SEAL HAD MALFUNCTIONED AND THE SUBSEQUENT OIL LOSS CAUSED THE ENGINE TO OVERHEAT AND ACTIVATE THE ENGINE FIRE DETECTION LO2L72 4T4  TRTA24CE   E26NE   5  CP10NE    
20070118000372007011800037SO  2007       1          18         2006FA0001141    120061120G21403716725         LINE                                    PIPER PA34  PA34200T    7103406SO  CONT  O520  TSIO520E    17040SO                              CABIN HEATER    LEAKING         B      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE074566Q                       347770241                               PILOT REPORTED FUEL SMELL IN THE CABIN WHEN CABIN HEATER IS ON.  FURTHER INVESTIGATION REVEALED A PIN HOLE CAUSED BY CORROSION IN THE CABIN HEATER FUEL LINE JUST AFT OF THE AFT SPAR CARRY THRU.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L72 3O3  O  A7SO    E8CE                 
20070118000382007011800038CE  2007       1          18         2006FA0001142    120061115G2731NAS302665170    CONTROL CABLE                           BEECH 90    C90         1152913CE  PWA   PT6   PT6*        52043EA                              ELEVATOR TRIM   KINKED          B  E81RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL03400BX                       LJ686                                   INVESTIGATED ELEVATOR TRIM OPERATIONS COMPLAINT.  FOUND FORWARD ELEVATOR TRIM CABLE, PN NAS302-66-5170, LOOSE AND OFF PULLEYS UNDER LT CABIN FLOOR AREA.  CABLE ASSY DAMAGED BY KINKING AND FRAYING FROM CONTACT WITH PULLEY SUPPORTS AND ADJACENT STRUCTURE.  ALSO FOUND PN 4000524-8508 ELEVATOR TRIM SERVO DAMAGED AND OPERATIONS ERRATIC.  MAINTENANCE RECORDS NOT MADE AVAILABLE, UNABLE TO DETERMINE PREVIOUS MAINTENANCE HISTORY FOR ELEVATOR TRIM SYSTEM.  HAVE NOTED SIMILAR DAMAGE IN OTHER SERIES AIRCRAFT.  USUALLY CAUSED BY CABLE MISROUTING OR LOW CABLE TENSION FOR AN EXTENDED PERIOD OF OPERATIONS.  (K)                                                                                                                      1L72 3T3  T  3A20    E2NE                 
20070116000642007011600064CE  2007       1          16         2006FA0001143    120061109G32601CH25           DOWNLOCK SWITCH                         BEECH 300   300BEECH    1152930CE                                                               MLG             INOPERATIVE     B  E81RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL038YN                         FL417                                   INVESTIGATED RED WARNING LIGHT ILLUMINATED IN LANDING GEAR CONTROL HANDLE WITH LANDING GEAR DOWN AND LOCKED.  FOUND NLG DOWNLOCK SWITCH.  S508 INOPERATIVE PN 101-3646289, MICROSWITCH-FREEPORT PN 1CH25.  REPLACED SWITCH AND ADJUSTED IAW MM.  LANDING GEAR POSITION/WARNING SYSTEM FUNCTIONAL TESTS NORMAL.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4T      A24CE                        
20070116000652007011600065SO  2007       1          16         2006FA0001144    120061110G7820                MUFFLER                                 MAULE M7235 M7235C      5460110SO  LYC   O540  IO540*      41532EA  HARTZLHCC3Y HCC3YR      GL  ENGINE          CRACKED         B  FTURO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA6555105165                    25104C      L3069248A   DY6641B         AIRCRAFT CAME IN FOR FIRST ANNUAL AFTER CERTIFICATION.  UPON VISUAL INSPECTION FOUND A CRACK ADJACENT TO THE WELD ON THE GUSSET/DOUBLER LOCATED ON THE LOWER PORTION OF THE MUFFLER AT THE EXHAUST OUTLET.  THE MUFFLER WAS PRESSURIZED AND VERIFIED THAT THE CRACK HAD EXTENDED INTO THE CAN.  MOST LIKELY CAUSED BY THE NORMAL FLEX AND ROTATION OF ENGINE OPERTATIONS.  COUPLED WITH THE METHOD OF ATTACHMENT OF THE EXHAUST PIPE.  (K)                                                                                                                                                                                                                                                                                                      1H71 3O3  ONC3A23    1E4     5  CP25EA    
20070109000442007010900044SO  2007       1          9          2006FA0001145    120061101G321330A04000091     DRAG LINK                               MAULE M7235 M7235C      5460110SO  LYC   O540  IO540*      41532EA  HARTZLHCC3Y HCC3YR      GL  RT MLG          MISINSTALLED    B  FTURO   OTHER                                                                                           W  INADEQUATE Q C                                                                NRNOT REPORTED   1                      EA6555105                       25104C      L3069248A   DY6641B         AIRCRAFT CAME IN FOR FIRST ANNUAL AFTER INSTALLATION.  ON INSPECTION FOUND MAIN GEAR DRAG LINK HAD NOT BEEN PROPERLY SEALED AT THE LOWER END ALLOWING WATER TO ENTER THE ASSEMBLY.  BECAUSE OF THE SEALANT WE ARE UNABLE TO TELL IF THE INSIDE OF THE TUBE HAS SOME SORT OF CORROSION PROTECTION.  MAY WANT TO CONSIDER DOING AWAY WITH THE SEALANT AND APPLYING A CORROSION PREVENTATIVE COMPOUND COUPLED WITH RECURRENT INSPECTION AND REAPPLICATION OF CPC.  (K)                                                                                                                                                                                                                                                                             1H71 3O3  ONC3A23    1E4     5  CP25EA    
20070116000752007011600075SO  2007       1          16         2006FA0001146    120061101G28102117X16         FUEL TANK                               MAULE M7235 M7235C      5460110SO  LYC   O540  IO540*      41532EA  HARTZLHCC3Y HCC3YR      GL  RT WING         LEAKING         B  FTURK   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      EA65551051655                   25104C      L3069248A   DY6641B         AIRCRAFT CAME IN FOR FIRST ANNUAL AFTER CERTIFICATION, THE OWNER OPERATOR REPORTED FUEL STAINING ON THE RT WING, ON INSPECTION THE FUEL TANK WAS FOUND TO BE LEAKING.  THE TANK WAS REMOVED AND UPON CLOSER INSPECTION 2 PIN HOLES WERE FOUND IN THE WELD SEAM, ONE BEING A LIGHT SEEP, THE OTHER LARGE ENOUGH TO PRODUCE A VISIBLE STAIN.  RECOMMEND THAT ALL FUEL TANKS BE PRESSURIZED AND LEAK CHECKED , AND THAT AN INSPECTOR PLACE THEIR (STAMP) INDICATING COMPLIANCE.  (K)                                                                                                                                                                                                                                                               1H71 3O3  ONC3A23    1E4     5  CP25EA    
20070118001262007011800126CE  2007       1          18         2006FA0001147    120061112G2797                WIRE                                    LEAR  55    55LEAR      5170702CE  GARRTTTFE731TFE7313     01518WP                              PITCH SERVO     SHORTED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO01550AK                       045                                     AIRCRAFT ABORTED TAKEOFF DUE TO BOTH STALL WARNINGS ILLUMINATED ON DEPARTURE ROLL.  C/B LEFT AND RIGHT STALL C/B POPPED.  AUTOPILOT, FLIGHT DIRECTOR AND PRIMARY YAW DAMPER INOPERATIVE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  F  A10CE   E6WE                 
20070118001272007011800127CE  2007       1          18         2006FA0001148    120061030G2510551900921       SEAT FRAME                              CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              COCKPIT         CRACKED         B      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA21550RB                       5500117                                 UPPER CHAIR BASE ASSY CRACKED AT CHAIR BACK ATTACH POINTS.  STRESS ON CHAIR BACK AND METAL FATIGUE PROBABLE CAUSE.  CHAIR WAS REPAIRED IAW STCC ST01042W STRUCTURAL SEAT REPAIR.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L72 4F4  F  A22CE   E1NE                 
20070118001282007011800128SO  2007       1          18         2006FA0001149    120061101G291021A09000204     HOSE                                    MAULE M7235 M7235C      5460110SO  LYC   O540  IO540*      41532EA  HARTZLHCC3Y HCC3YR      GL  HYD SYSTEM      MISMANUFACTURED B  FTURO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA655510586                     25104C      L3069248A   DY6641B         AIRCRAFT CAME IN FOR FIRST ANNUAL AFTER CERTIFICATION.  ON INSPECTION HYDRAULIC FLUID WAS FOUND TO BE COMING FROM THE FORWARD FUSELAGE DRAIN.  UPON REMOVAL OF THE FLOOR THE INSULATION WAS FOUND TO BE SATURATED WITH HYDRAULIC FLUID.  THE SYSTEM WAS REFILED AND TROUBLESHOT, THE LEAK WAS TRACKED TO A HOSE.  INSPECTION OF THE HOSE REVEALED THAT THE HOSE END WASN`T PROPERLY INSTALLED RESULTING IN THE FLUID LEAK.  THIS WAS A RESULT OF IMPROPPER ASSEMBLY OF THE HOSE BY MFG AND SHOULD HAVE BEEN CAUGHT DURING PRESSURE TESTING AFTER INITIAL ASSY.  (K)                                                                                                                                                                             1H71 3O3  ONC3A23    1E4     5  CP25EA    
20061212003202006121200320CE  2006       12         12         2006FA0001150    120061017G3230998100227       LOCK PLATE      BEECH                   BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA                              MLG             MISINSTALLED    D  PFBVO   OTHER                                                                                           W  INADEQUATE Q C                                                                NRNOT REPORTED   1                      EA27528WG                       BB151                                   DURING POST ACCIDENT INSPECTION OF RT AND LT MAIN LANDING GEAR DRAG LEGS, LOCK PLATES WERE FOUND MOUNTED WITH THE BEVEL AT THE NOSE OF THE PLATE FACING UP.  INSPECTION OF 5 OTHER AC FOUND THE BEVEL FACING DOWN.  REVIEW OF CURRENT REPS COMPONENT MM IS INCONCLUSIVE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1L72 4T4  T  A24CE   E4EA                 
20061208001822006120800182CE  2006       12         8          2006FA0001151    120061207G531460410025601     KEEL                                    BEECH 60    B60         1153605CE                                                               FUSELAGE        CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL193876C3004                   P513                                    DURING ANNUAL INSPECTION, STIFFENER PART NUMBER 60-410025-51 LOCATED UNDER THE NOSE BAGGAGE FLOOR ON THE RIGHT SIDE AT STATION 67 BETWEEN THE MAIN AND STANDBY INVERTER WAS FOUND CRACKED AROUND THE HI-LOK FASTENER HOLES.  REMOVAL OF THE STIFFENER ALLOWED FURTHER INSPECTION OF THE KEEL PART NUMBER 60-410025-601, WHICH REVEALED CRACKS IN THE WEB WHICH WERE PREVIOUSLY OBSCURED BY THE INSTALLED STIFFENER.  THE MIRROR IMAGE STIFFENER PART NUMBER 60-410025-49 ON THE LEFT SIDE OF THE AIRCRAFT REVEALED SIMILAR CRACKS WITH NO DAMAGE TO THE KEEL.                                                                                                                                                                                   1L72 3O      A12CE                        
20061212002992006121200299WP  2006       12         12         2006FA0001152    220061108G723030721631        DAMPER                                  LEAR  35    35LEAR      5170600CE  GARRTTTFE731TFE73122B   01518WP                              NR 1 ENGINE     BROKEN          B  UO2RO   OTHER                                                                                           E  VIBRATION/BUFFET                                                              NRNOT REPORTED   1                      GL19573RL                       153         P74494                      AIRCRAFT ARRIVED 10/31/2006 TO TROUBLESHOOT A RUMBLE FROM THE NR 1 ENGINE.  UPON INVESTIGATION, FOUND 1 FAN BLADE TO HAVE A BROKEN MIDSPAN DAMPER. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  F  A10CE   E6WE                 
20061208001832006120800183CE  2006       12         8          2006FA0001153    120061207G53146041002551      STIFFENER                               BEECH 60    B60         1153605CE                                                               FUSELAGE        CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL193876C3004                   P513                                    DURING ANNUAL INSPECTION, STIFFENER PART NUMBER 60-410025-51 LOCATED UNDER THE NOSE BAGGAGE FLOOR ON THE RIGHT SIDE AT STATION 67 BETWEEN THE MAIN AND STANDBY INVERTER WAS FOUND CRACKED AROUND THE HI-LOK FASTENER HOLES.  REMOVAL OF THE STIFFENER ALLOWED FURTHER INSPECTION OF THE KEEL PART NUMBER 60-410025-601, WHICH REVEALED CRACKS IN THE WEB WHICH WERE PREVIOUSLY OBSCURED BY THE INSTALLED STIFFENER.  THE MIRROR IMAGE STIFFENER PART NUMBER 60-410025-49 ON THE LEFT SIDE OF THE AIRCRAFT REVEALED SIMILAR CRACKS WITH NO DAMAGE TO THE KEEL.                                                                                                                                                                                   1L72 3O      A12CE                        
20061212003132006121200313NE  2006       12         12         2006FA0001154    220061113G7250RB211524G19     DISC                                                                       RROYCERB211 RB211524G19      NE                              ENGINE          WORN            B  QEMYO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA35     573507399                          13048                       (REF NR: MDR/004/06) STRIP EXAMINATION REVEALED HEAVY RUBS TO THE LP1 TURBINE DISC AND TO THE LP1 AND LP2 TURBINE BLADES.  INITIAL EXAMINATION HAS FAILED TO IDENTIFY THE CAUSE OF THE BLADE AND DISC CONTACT ALL SETTINGS APPEARING NORMAL  A REVIEW OF SERVICE OPERATION HAS FAILED TO IDENTIFY ANY INCREASE IN VIBRATION IN SERVICE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                           4  F          E30NE                
20061212003042006121200304WP  2006       12         12         2006FA0001155    120061009G5311                FRAME                                   LKHEED1011  10113853    5265020WP  RROYCERB211 RB21122*    54555NE                              FUSELAGE        CRACKED         B  RJAYK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA33753DA                       193W1189                                (REF NR: 06DA063)  DURING C-CHECK, MAINTENANCE TASK 53-02-1000 INSP FS 983 FRAME.  A CRACK, 3 INCHES) FOUND AT LT, BY A CLOSE VISUAL INSP AND CONFIRMED BY NDT.  NRC NR 546 RAISED FOR CORRECTIVE ACTION.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L73 4F4  F  A23WE   A12EU                
20061212002732006121200273CE  2006       12         12         2006FA0001156    120061117G2750                FITTING                                 BEECH 65    A65         1152803CE                                                               T/E FLAP        SHEARED         B  YCYRO   OTHER                                                                                           F  FLT CONT AFFECTED                                                             UKUNKNOWN        1                      SO19V2LDO                       LC291                                   (REF NR: MOR NR OCC442)  OPERATED FLIGHT NR 101, VFR CONDITIONS, FLIGHT AND APPROACH LANDING WAS NORMAL.  AFTER LANDING, ROLLOUT FLAPS WERE RETRACTED.  WHEN EXITING THE AC IT WAS NOTICED THAT THE INNER FLAP ON THE PORT SIDE WAS STILL DOWN.  THE FLAP WAS MANUALLY RESET TO ZERO, AND THE AIRCRAFT WAS FLOWN BACT TO DEPARTURE AIRPORT.  A FLAPLESS LANDING WAS CARRIED OUT.  MAINTENANCE FOUND THAT THE LT IB FLAP DRIVE ASSY HAD FAILED.  THE 2 LUGS THAT TRANSFER CABLE MOVEMENT 90 DEGREES INTO ACTUATOR MOVEMENT HAD SHEARED.  THE LT IB FLAP COULD BE DEPLOYED FROM THE (UP) TO THE (DOWN) POSITION, BUT HAD TO BE RESET TO THE (UP) POSITION MANUALLY.  THE LT OB, RT IB AND OUB FLAP DRIVE ASSY`S, FLAP GEAR BOX AND DRIVE  ASSY, PN1L72 3O      3A20                         
20061212002952006121200295EU  2006       12         12         2006FA0001157    120060524G2822SC402           PUMP                                    BRAERO1000  BAE1251000  1500287EU  PWA   305   PW305            NE                              FUEL SYSTEM     FAILED          B  UO2RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL1946WC      247               259028                                  THREE FUEL BOOST PUMPS IN OVERHAULED CONDITION, SAME PART NUMBER, ORDERED FROM THE SAME VENDER HAVE FAILED AFTER SHORT TIME ON SAME AIRCRAFT USED ON LT AND RT SIDES. 1) FUEL BOOST PUMP OVERHAULED CONDITION SN 11A557 FAILED 5/24/06 AFTER 247 HOURS.  2) FUEL BOOST PUMP OVERHAULED CONDITION SN 9AU160 FAILED 5/11/06 AFTER 232 HOURS.  3) FUEL BOOST PUMP OVERHAULED CONDITION SN 1AK23 FAILED 11/17/06 AFTER 157 HOURS.  (K)                                                                                                                                                                                                                                                                                                              2L72 4F4  FRTA3EU    E35NE                
20061212002932006121200293EU  2006       12         12         2006FA0001158    120060511G2822SC402           PUMP                                    BRAERO1000  BAE1251000  1500287EU  PWA   305   PW305            NE                              FUEL SYSTEM     FAILED          B  UO2RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL1946WC 232                                                            THREE FUEL BOOST PUMPS IN OVERHAULED CONDITION, SAME PN, ORDERED FROM SAME VENDOR HAVE FAILED AFTER SHORT TIME ON SAME AIRCRAFT USED ON LT AND RT SIDES.  1) FUEL BOOST PUMP OVERHAULED CONDITION SN 11A557 FAILED 5/24/06 AFTER 247 HOURS.  2) FUEL BOOST PUMP OVERHAULED CONDITION SN 9AU160 FAILED 5/11/06 AFTER 232 HOURS.  3) FUEL BOOST PUMP OVERHAULED CONDITION SN 1AK23 FAILED 11/17/06 AFTER 157 HOURS.  (K)                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA3EU    E35NE                
20061212003012006121200301EU  2006       12         12         2006FA0001159    120061117G2822SC402           PUMP                                    BRAERO1000  BAE1251000  1500287EU  PWA   305   PW305            NE                              FUEL SYSTEM     FAILED          B  UO2RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL1946WC                        259028                                  THREE FUEL BOOST PUMPS IN OVERHAULED CONDITION, SAME PN, ORDERED FROM THE SAME VENDOR HAVE FAILED AFTER SHORT TIME ON SAME AIRCRAFT USED ON LT AND RT SIDES.  1) FUEL BOOST PUMP OVERHAULED CONDITION SN 11A557 FAILED 5/24/06 AFTER 247 HOURS.  2) FUEL BOOST PUMP OVERHAULED CONDITION SN 9AU160 FAILED 5/11/06 AFTER 232 HOURS.  3) FUEL BOOST PUMP OVERHAULED CONDITION SN 1AK23 FAILED 11/17/06 AFTER 157 HOURS.  (K)                                                                                                                                                                                                                                                                                                                      2L72 4F4  FRTA3EU    E35NE                
20061213000612006121300061WP  2006       12         13         2006FA0001160    120061104G6210                HOUSING         ROBSIN                  ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540*      41532EA                              M/R BLADE       LEAKING         D      O   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      NM05424SH1353       1989C       10877                                   FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3O3  O  H11NM   1E4                  
20070104000742007010400074WP  2007       1          4          2006FA0001161    120061109G6210C1561           BOOT            ROBSIN                  ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540*      41532EA                              MAIN ROTOR BLADELEAKING         D      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      NM05424SH1353       1989C       10877                                   FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3O3  O  H11NM   1E4                  
20070109000452007010900045CE  2007       1          9          2006FA0001163    120060823G526012115041        CABLE                                   CESSNA210   T210M       2073451CE  CONT  O520  TSIO520*    17040SO                              PAX DOOR STEP   BROKEN          H      O   OTHER                                                                                           S  AFFECT SYSTEMS                                                                LDLANDING        1                      WP176169N1000                   21062940                                THE PILOT EXTENDED THE LANDING GEAR PRIOR TO LANDING, AND THE NOSEGEAR WOULD NOT EXTEND INTO THE DOWN-AND-LOCKED POSITION (THE MAINS LOCKED).  DURING LANDING, THE NOSEGEAR COLLAPSED.  POST INCIDENT INSPECTION SHOWED THAT THE PASSENGER STEP CABLE BROKE AT THE FORWARD PULLEY AND INTERTWINED WITH THE NOSE GEAR LINKAGE, NOT ALLOWING IT TO LOCK.                                                                                                                                                                                                                                                                                                                                                                                          1H71 3O3  O  3A21    E8CE                 
20070104000752007010400075WP  2007       1          4          2006FA0001164    120061204G6210C1561           BOOT            ROBSIN                  ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540*      41532EA                              MAIN ROTOR BLADELEAKING         D      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      NM05424SH1408       1989C       10877                                   FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3O3  O  H11NM   1E4                  
20070108001742007010800174WP  2007       1          8          2006FA0001165    120061203G6210C1561           BOOT            ROBSIN                  ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540*      41532EA                              M/R BLADE       LEAKING         D      O   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      NM05424SH1353       1989C       10877                                   FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3O3  O  H11NM   1E4                  
20070108001762007010800176WP  2007       1          8          2006FA0001166    120061104G6210C1561           BOOT            ROBSIN                  ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540*      41532EA                              M/R BLADE       LEAKING         D      O   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      NM05424SH1353       1989C       10877                                   FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3O3  O  H11NM   1E4                  
20070108001792007010800179WP  2007       1          8          2006FA0001167    120061204G6210C1561           BOOT            ROBSIN                  ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540*      41532EA                              M/R BLADE       LEAKING         D      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      NM05424SH1408       1905C       10877                                   FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3O3  O  H11NM   1E4                  
20070108001832007010800183WP  2007       1          8          2006FA0001168    120061204G6210C1561           BOOT            ROBSIN                  ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540*      41532EA                              M/R BLADE       LEAKING         D      O   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      NM05511CC54         3424        10173                                   FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3O3  O  H11NM   1E4                  
20070108001842007010800184WP  2007       1          8          2006FA0001169    120061204G6210C1561           BOOT            ROBSIN                  ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540*      41532EA                              M/R BLADE       LEAKING         D      O   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      NM05511CC54         3425        10173                                   FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3O3  O  H11NM   1E4                  
20070108001902007010800190WP  2007       1          8          2006FA0001170    120061117G5340269A5472        BRACKET         HUGHES                  HUGHES269   269C        4470504WP  LYC   O360  HIO360C1A   41514EA                              FUSELAGE        BROKEN          B      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW17110472701 29                211031      L2209751A                   ONE OF THE BELT DRIVE CLUTCH ACTUATION SYSTEM CABLE PULLEY BRACKETS (1 OF 2 P/N 269A5472) BROKE CLEAN ACROSS BETWEEN THE PULLEY AND ITS FRAME MOUNT HOLES DURING THE PROCESS OF ENGAGING THE ROTOR SYSTEM. DURING THE SUBSEQUENT ATTEMPTED TAKEOFF THE OPERATOR NOTED THAT ROTOR RPM WOULD BLEED OFF RAPIDLY DUE TO DRIVE BELT SLIPPAGE WHEN THE COLLECTIVE CONTROL WAS RAISED. THE OPERATOR ABORTED THE TAKEOFF ATTEMPT, SHUTDOWN THE AIRCRAFT, AND INVESTIGATED THE PROBLEM THEN NOTIFIED REPAIR PERSONNEL. THE BRACKET AND THE PULLEY (P/N MS20219-4) WERE THE ONLY PARTS DAMAGED IN THIS ASSEMBLY AS A RESULT OF THIS FAILURE.                                                                                                              1G71 3O3  O  4H12    1E10                 
20070109000302007010900030WP  2007       1          9          2006FA0001171    120061204G6210C1561           BOOT            ROBSIN                  ROBSINR44   R44         7640120WP  LYC   O540  O540*       41532EA                              M/R BLADE       LEAKING         D      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      NM057133E408        5068A       0573                                    FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3O3  O  H11NM   E295                 
20070109000312007010900031WP  2007       1          9          2006FA0001172    120061204G6210C1561           BOOT            ROBSIN                  ROBSINR44   R44         7640120WP  LYC   O540  O540*       41532EA                              M/R BLADE       LEAKING         D      O   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      NM057133E408        5073A       0573                                    FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3O3  O  H11NM   E295                 
20070109000522007010900052WP  2007       1          9          2006FA0001173    120061203G6210C1561           BOOT            ROBSIN                  ROBSINR44   R44         7640120WP  LYC   O540  O540F1A5    41532EA                              M/R BLADE       LEAKING         D      O   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      NM0569KA 191        4272A       1182                                    FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3O3  O  H11NM   E295                 
20070109000532007010900053WP  2007       1          9          2006FA0001174    120061203G6210C1561           BOOT            ROBSIN                  ROBSINR44   R44         7640120WP  LYC   O540  O540F1A5    41532EA                              M/R BLADE       LEAKING         D      O   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      NM0569KA 191        4268A       1182                                    FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3O3  O  H11NM   E295                 
20070109000542007010900054WP  2007       1          9          2006FA0001175    120061203G6210C1561           BOOT            ROBSIN                  ROBSINR44   R44         7640120WP  LYC   O540  O540F1A5    41532EA                              M/R BLADE       LEAKING         D      O   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      NM0569KA 191        4268A       1182                                    FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3O3  O  H11NM   E295                 
20070205000532007020500053WP  2007       2          5          2006FA0001176    120061203G6210C1561           BOOT            ROBSIN                  ROBSINR44   R44         7640120WP  LYC   O540  O540F1A5    41532EA                              M/R BLADE       LEAKING         D      O   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      NM0569KA 191        4268A       1182                                    FLUID LEAKING FROM MAIN ROTOR BLADE PITCH BEARING HOUSING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3O3  O  H11NM   E295                 
20070104000622007010400062SO  2007       1          4          2006FA0001177    120061130G5711                STRUT                                   PIPER J3    J3          7100502SO                                                               RIGHT WING      CORRODED        G      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      NM05                                                                    RT STRUT WAS DAMAGED FROM LOWERING A BI-FOLD HANGER DOOR ON THE WING TIP.  THE STRUT WAS MANUALLY SEPARATED WERE EXTENSIVE CORROSION WAS FOUND INSIDE THE WING STRUT.  THE PLANE HAS SET IDLE FOR 3 YEARS OUT OF ANNUAL INSPECTION. THE LAST ANNUAL INSPECTION PERFORMED INCLUDED COMPLYING WITH AD 99-01-05 WITH NO DISCREPANCIES NOTED.                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3O      ATC660                       
20070108001422007010800142CE  2007       1          8          2006FA0001178    120061212G8120227450          CLAMP                                   CESSNA421   421         2076010CE  CONT  O520  GTSIO520N   17032SO                              TURBOCHARGER    CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW99     1366                                                           DURING PROGRESSIVE INSPECTION FOUND LT ENGINE TURBOCHARGER TO TAILPIPE CLAMP CRACKED ALONG CIRCUMFERENCE, APPROX. 4 INCH CRACK.  FOUND SAME PN CLAMP ON THE RT ENGINE OF THIS AIRCRAFT TO BE CRACKED 7 HOURS PREVIOUSLY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L72 3O3  ORTA7CE    E7CE                 
20070108001732007010800173EA  2007       1          8          2006FA0001179    220061205G8530                CONNECTING ROD                          PIPER PA32  PA32RT300   7103215SO  LYC   O540  IO540K1G5   41532EA                              ENGINE          FAILED          C      A   UNSCHED LANDING                                                                                 Y  ENGINE STOPPAGE                                                               CLCLIMB          1                      GL272148N1965                   32R7985069  1892548A                    INTERNAL ENGINE FAILURE, CYLINDERS 2 AND 4 CONNECTING RODS FAILED. ENGINE WAS ORIGINAL TO THE AIRCRAFT (1979).                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L71 3O3  O  A3SO    1E4                  
20070108003052007010800305NM  2007       1          8          2006FA0001180    120061207G790030C208301       TRANSDUCER                              AMD   FALC50FALCON2000  2730170NM  PWA   306   PW306B           NE                              RT ENGINE OIL   FALSE INDICATIONC      O   OTHER                                                                                           N  FALSE WARNING                                                                 NRNOT REPORTED   1                      NM07                            028         CF0088                      RT ENGINE OIL TRANSDUCER FAILURE WHICH GAVE FALSE ENGINE OIL INDICATION WHICH CAUSED BY AIRCRAFT OPERATIONS MANUAL CHECK LIST ENGINE SHUTDOWN AND SINGLE ENGINE LANDING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2K72 4F4  FRTA50NM   E35NE                
20070108003142007010800314NM  2007       1          8          2006FA0001181    120061212G80113617712         HOUSING                                 DOUG  MD80  MD83        3023681NM                                                               STARTER         CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP05                                                                    STARTER HOUSING FOUND CRACKED DURING DYE PENETRANT INSPECTION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F    RT                             
20070108003182007010800318GL  2007       1          8          2006FA0001182    320061213G6114                HUB                                     PIPER PA28  PA28181     7102807SO  LYC   O360  O360A4M     41514EA  MCAULY1A170 1A170*      GL  PROPELLER       CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA112112K1839                   287990234   L2600423A   RK022           DURING ANNUAL INSPECTION FOUND CRACK EXTENDING THROUGH THE HUB AT ONE OF THE MOUNTING BOLT HOLES.  CRACK GOES COMPLETLEY THROUGH THE HUB TO THE INNER BORE OF THE HUB. NO HISTORY OF PROP STIKE OR ANY OTHER VISUAL DAMAGE TO THE PROPELLER. THIS PROPELLER INSTALLED WITH STC NR SA779NE. PROPELLER REMOVED FROM AIRCRAFT AND SENT FOR FURTHER STUDY IAW MFG REQUEST.                                                                                                                                                                                                                                                                                                                                                                          1L71 3O3  O  2A13    E286    5  NP857     
20070108003272007010800327EU  2007       1          8          2006FA0001183    120061208G251076201113        BRACKET                                 EXTRA EA300 EA300       70218DIEU  LYC   O540  AEIO540*         EA                              SEAT BACKREST   CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15497AF1600 44                072                                     DURING A ROUTINE INSPECTION IT WAS NOTICED THE 76201.113 TOUNGE BRACKETS LT AND RT WHICH ATTACH THE REAR SEAT BACKREST TO THE LOWER SEAT ASSEMBLY WERE CRACKED THRU THE BOLT HOLES ATTACHING TO THE BACKREST. FURTHER CLOSE EXAMINATION (REMOVED UPHOLSTERY)OF THE REMOVED BACKREST ASSEMBLY REVEALED THE SEAT BACK WAS SIGNIFICANTLY CRACKED IN THE AREA OF THE UPPER BACKREST WHERE THE SEAT BACKREST ANGLE CAN BE ADJUSTED.  RECOMMEND CLOSER INSPECTION OF THE AFFECTED PARTS BE ADDED TO THE 100HR AND 1000HR INSPECTION CHECKLISTS.                                                                                                                                                                                                       1M71 3O3  ONCA67EU   1E4                  
20070108003432007010800343NE  2007       1          8          2006FA0001184    220061129G7323                SPRING          WOODWARD                                                   GE    CF6   CF650*      30018NE                              GOVERNOR        BROKEN          C      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW99                WYG13493                                            COMPRESSOR DISCHARGE PRESSURE RESTORING SPRING P/N 3018-248 HAS FRACTURED CLOSE TO THE SPRING SEAT 9.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  4  F          E23EA                
20070108003462007010800346NE  2007       1          8          2006FA0001185    220061129G7323                SPRING          WOODWARD                                                   GE    CF6   CF650*      30018NE                              GOVERNOR        BROKEN          C      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW99                WYG13493                                            COMPRESSOR DISCHARGE PRESSURE RESTORING SPRING P/N 3018-248 HAS FRACTURED CLOSE TO THE SPRING SEAT 9.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  4  F          E23EA                
20070109000462007010900046SO  2007       1          9          2006FA0001186    120061213G2150                TURBINE WHEEL                           GULSTMG1159 GIV         3980115SO                                                               ACM             SEIZED          C      H   DEACTIVATE SYST/CIRCUITS                                                                        O  OTHER                                                                         LDLANDING        1                      WP23596CW4541                   1145                                    AIR CYCLE MACHINE TURBINE WHEEL HAS SEIZED CAUSING INOPERATIVE AIR CONDITIONING SYSTEM.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F    RTA12EA                        
20070109000512007010900051EU  2007       1          9          2006FA0001188    120061202G5530                RIVET                                   SOCATATB9   TB9         8680694EU  CONT  C125  C125*       17011SO                              VERTICAL STAB   LOOSE           H      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW09557J                        1326                                    DURING THE PRE-FLIGHT INSPECTION FOR A LOCAL TRAINING FLIGHT, THE BLIND RIVETS LOCATED HALFWAY UP VERTICAL FIN WERE FOUND TO BE MAKING ALUMINUM OXIDE (DIRT TRAILS) ON BOTH SIDES OF THE VERTICAL FIN.  THIS CONDITION IS INDICATIVE OF A POTENTIALLY LOOSE RIVET OR CRACKED INNER RIB.  MFG SB 10-083 REQUIRES THIS TYPE OF RIVET (CHERRY-MAX) AT THIS LOCATION.  SUSPECT OTHER AIRCRAFT HAVE SAME ISSUE.                                                                                                                                                                                                                                                                                                                                      1L71 3O3  ONTAS1EU   E236                 
20070109000572007010900057GL  2007       1          9          2006FA0001189    120061212G7921P010904         OIL COOLER                              AMTR  AMD   ALARUSCH2T  0033001GL  LYC   O235  O235*       41505EA                                              LEAKING         D      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  TXTAXI/GRND HDL  1                      GL13216LF60                     201034                                  OWNER REPORTED THAT AFTER FLYING AIRCRAFT, THERE APPEARED TO BE OIL LEAKING FROM UNDER COWLING.  OIL LEVEL WAS CHECKED AND FOUND TO BE DOWN TO ONLY 3 QUARTS LT.  AFTER REMOVAL OF COWLING AND INSPECTION, IT WAS FOUND THAT MOST OF THE OIL LEAKAGE APPEARED TO BE AROUND THE OIL COOLER. OIL COOLER LINES WERE DISCONNECTED AND OIL COOLER WAS PRESSURIZED WITH ABOUT 30 PSI OF AIR PRESSURE.  A SMALL HOLE WAS FOUND IN THE UPPER RT EDGE OF OIL COOLER AT A WELD SEAM.  THIS AIRCRAFT HAS ONLY ABOUT 60 HOURS TOTAL TIME SINCE NEW.  AN ANNUAL INSPECTION ABOUT 2 HOURS AGO DID NOT REVEAL ANY OIL LEAKAGE.  IT APPEARS THAT THE CAUSE WAS A DEFECTIVE WELD IN THE MANUFACTURING OF THE OIL COOLER.                                         1L71   3  O  EXPA1L71E223                 
20070109000582007010900058EU  2007       1          9          2006FA0001190    120061202G5751                RIB                                     SPHRTHCIRRUSCIRRUS      38019VCEU                                                               AILERON         CRACKED         H      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW095557 8255                   37                                      DURING PRE-FLIGHT INSPECTION FOR TRAINING FLIGHT, IDENTIFIED CRACKS ON OUTER RIB CAPS ON BOTH AILERONS.  CRACKS APPEAR TO BE ORIGINATING AT THE ATTACHMENT RIVETS LOCATED AT THE EDGE OF THE AILERONS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1K00         G19EU                        
20070109000492007010900049SO  2007       1          9          2006FA0001192    220061213G8530TISN712BCA221   CYLINDER                                CESSNA340   340A        2076405CE  CONT  O520  TSIO520NB   17040SO  HARTZLHCC3Y PHCC3YF2    GL  ENGINE          CRACKED         C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP254155A652                    340A1001    509812                      COMPLIANCE WITH ENGINE COMPONENTS, INC. MANDATORY SB06-2 DISCLOSED CRACKED CYLINDER IN RT ENGINE WITH OBVIOUS LEAKAGE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L72 3O3  O  3A25    E8CE    5  CP25EA    
20070108001922007010800192CE  2007       1          8          2006FA0001193    120061218G214070893           PUMP            JANITROL    B4500       BEECH 58    58          1152740CE  CONT  O550  IO550*           SO                              HEATER          BURNED OUT      B      A   UNSCHED LANDING                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      CLCLIMB          1                      WP25870JA1935                   TH2036                                  SMOKE IN THE COCKPIT, AND ELECTRICAL BURNING SMELL WERE OBSERVED AFTER TAKEOFF, AFTER THE GEAR WAS RETRACTED. THE HEATER HAD BEEN IN OPERATION APPROXIMATELY 30 MINUTES BEFORE TAKEOFF, WITH NO SMOKE OR SMELL OBSERVED.  THE HEATER WAS TURNED OFF, AND THE SMOKE DISSIPATED. THE AIRCRAFT RETURNED TO LAND.  THE HEATER FUEL PUMP, LOCATED IN THE NOSE GEAR WELL, WAS FOUND TO BE CHARRED.  WHEN THE GEAR IS RETRACTED AND THE GEAR DOORS ARE CLOSED, THERE WOULD BE DIFFERENT AIR-FLOW IN THE GEARWELL, POSSIBLY CAUSING A HIGHER PRESSURE IN THE GEARWELL AND FORCING AIR INTO THE CABIN, PAST THE BOOTS FOR THE NOSE GEAR RETRACT ROD AND STEERING LINKAGES.  THIS IS AT LEAST THE THIRD OCCURRENCE OF A BURNED PUMP IN A FLEET OF 11 LIKE 1L72 3O3  O  3A16    E3SO                 
20070118001232007011800123NE  2007       1          18         2006FA0001195    120061128G6220641026000042    DAMPER                                  SKRSKYS64   S64E        8142604NE                                                                               BROKEN          B  JYDRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM09CGESG                       64065                                   (REF: MDR06-093) DAMPER WAS REMOVED FROM THE AIRCRAFT DUE TO, THE PISTON PN 6410-26005-104, SN 550 FOUND BROKEN AFTER SHUTDOWN OF HELICOPTER.  THE PISTON ROD BROKE NEAR THE FORK ASSEMBLY, PN 6410-26211-041 AND APPEARS TO BE BROKEN AT THREADS.  DAMPER WAS INSTALLED ON MRH PN 6410-20004-033, SN A2-013.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                              2G72 4U      H4EA                         
20070116000132007011600013CE  2007       1          16         2006FA0001196    120061129G291090E551701064    LINE            CESSNA                  CESSNA500   500CESSNA   2076602CE  PWA   JT15  JT15D1      52060NE                              BRAKE ASSY      CORRODED        B  AKGRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE05501LH                       5000342                                 INVESTIGATING SOFT BRAKE CONDITION IT WAS NOTED THAT BRAKE FLUID WAS LEAKING FROM AROUND THE BELLY BEACON AND THE BEACON LENS WAS FULL OF FLUID.  REMOVED THE INTERIOR AND THE CENTER AISLE FLOOR PANELS.  HYDRAULIC FLUID WAS NOTED DRIPPING FROM RIDGE BRAKE LINE TO THE RT BRAKE.  PN 90E5517010-64 AT FS248.1.  MFG INSTALLED AIR-CONDITIONING COLD AIR DUCT IS TY-RAPED TO THE BRAKE FLUID LINES.  BELLY BEACON IS DIRECTLY BELOW THE CORROSION AND THE BRAKE FLUID LEAKAGE.  THE AIRCRAFT IS NOT EQUIPPED WITH BELLY DRAINS.  THE CONDENSATION LIES IN THE BELLY OF THE AIRCRAFT AND THE BEACON CREATES HEAT AND THE HUMIDITY CAUSES CORROSION ON COMPONENT PARTS IN THE UNDER FLOOR AREA.  MFG PROBABLY SHOULD ENGINEER A DRAINAGE SYSTEM1L72 4F4  F  A22CE   E1NE                 
20070116000162007011600016CE  2007       1          16         2006FA0001197    120060918G5343                TRUSS                                   AYRES S2    S2R         7630202CE                                                               MLG             BROKEN          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      AL0332LF 9000                   5089R                                   UPPER TRUSS TO SHOCK STRUT BROKE OFF GEAR LEG, ALLOWING LANDING GEAR TO COLLAPSE.  THIS AIRCRAFT HAS BEEN USED FOR FUEL HAULING AND IS LANDING WITH HEAVY LOADS.  IT APPEARS A SMALL CRACK IN 1 TRUSS TUBE DEVELOPED AND EVENTUALLY FAILED, CAUSING TOTAL FAILURE OF THE LANDING GEAR LEG.  RECOMMEND DYE PENETRANT INSPECTION OF GEAR LEGS ON AIRCRAFT CONSISTANTLY LANDING WITH HEAVY LOADS EVERY 200 TO 300 HOURS.  (K)                                                                                                                                                                                                                                                                                                                      1L71 3R    NCA4SW                         
20070116000142007011600014NM  2007       1          16         2006FA0001198    120060912G5540173A01038       RUDDER                                  BOEING737   73776N      13844CHNM  GE    CFM56 CFM56*      13802NE                                              DAMAGED         B  I6XRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL11279AT                       32666                                   RUDDER DAMAGED DUE TO LIGHTENING STRIKE WHILE AIRCRAFT WAS ON GROUND.  DETAILED INFORMATION CONCERNING THIS REPAIR CAN BE FOUND ON (NR 10981-3600-0001). (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F4  FRTA16WE   E2GL                 
20070116000192007011600019EA  2007       1          16         2006FA0001199    220061003G8520STD21C7         SCREW                                   PIPER PA24  PA24250     7102404SO  LYC   O540  O540A1A     41532EA                              IDLR GEAR       FAILED          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA175097P                       24107       L11240                      A POST ACCIDENT INVESTIGATION IDENTIFIED THAT THE CRANKSHAFT IDLER GEAR WAS MISSING SEVERAL TEETH.  FURTHER EXAMINATION REVEALED THAT THE SCREWS HOLDING THE CRANKSHAFT IDLER GEAR SHAFT HAD FAILED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L71 3O3  O  1A15    E295                 
20070109000052007010900005CE  2007       1          9          2006FA0001200    120061205G5330030A326633      ACCESS PANEL                            MTSBSIMU2   MU2B60      5780460CE  GARRTTTPE331TPE331*     01514WP                              FUSELAGE        CORRODED        D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL25215MH                       1544SA                                  DRAIN HOLE IN COVER NOT BEING LOCATED PROPERLY CAUSES WATER TO LAY IN AFT.  FLANGE OF NEXT FRAME FWD CAUSING CORROSION.  (DRAIN HOLE NEEDS TO BE IN FRAME RADIUS.  (PRIMARY STRUCTURE).  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H72 3T3  TRTA10SW   E2WE                 
20070116000742007011600074CE  2007       1          16         2006FA0001201    120060630G8120C2950010101     TURBOCHARGER                            CESSNA210   T210N       2073456CE  CONT  O520  TSIO520*    17040SO                              ENGINE          FAILED          B  H5GRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA076363L32                     21064703                                NEW TURBO ASSY WAS INSTALLED 3/27/2006.  (3) MONTHS LATER ON 6/30/06 (32 HOURS TT) THE TURBO SHAFT TIGHTENED UP ENOUGH TO NOT PRODUCE TAKEOFF POWER ON NEXT FLIGHT.  OIL PRESSURE AND OIL VOLUME DELIVERED TO TURBO BEARINGS WAS VERIFIED TO BE ADEQUATE.  CUSTOMER PROCEDURES FOR COOL DOWN/ SPOOL DOWN OF TURBO AFTER TAXI WERE VERIFIED TO BE CONSISTENT WITH MFG POH RECOMMENDED PROCEDURES.  NEW TURBO WAS INSTALLED AND (4) MONTHS (41 HOURS TURBO TT) LATER IT DID THE SAME THING.  M OR D REPORT SUBMITTED THIS DATE ALSO.   (K)                                                                                                                                                                                                        1H71 3O3  O  3A21    E8CE                 
20070116000682007011600068CE  2007       1          16         2006FA0001202    120061006G8120C2950010101     TURBOCHARGER                            CESSNA210   T210N       2073456CE  CONT  O520  TSIO520*    17040SO                                              FAILED          B  H5GRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA076363L41                     21064703                                NEW TURBO ASSY WAS INSTALLED 6/30/06.  FOUR MONTHS LATER ON 10/6/06 (41 HOURS TT) THE TURBO SHAFT TIGHTENED UP ENOUGH TO NOT PRODUCE TAKEOFF POWER ON NEXT FLIGHT.  OIL PRESSURE AND OIL VOLUME DELIVERED TO TURBO BEARINGS WAS VERIFIED TO BE ADEQUATE.  CUSTOMER PROCEDURES FOR COOL DOWN/SPOOL DOWN OF TURBO AFTER TAXI WERE VERIFIED TO BE CONSISTENT WITH POH RECOMMENDED PROCEDURES.  THIS IS THE (2ND) TURBO IN 7 MONTHS TO DEVELOP THIS PROBLEM.  MFG HAS NUMEROUS REPORTS OF THIS SAME PROBLEM.  IT WOULD SEEM APPROPRIATE TO RE-EVALUATE THE ENGINEERING AND OR MFG OF THE SHAFT, BEARINGS, CLEARANCES, ETC OF THE TURBO.  (K)                                                                                                        1H71 3O3  O  3A21    E8CE                 
20070118000932007011800093SW  2007       1          18         2006FA0001203    120061007G3213109152          STRUT                                   AIRPTSA     A9B         0144206SW  LYC   O540  TIO540*     41532EA                              MLG             FAILED          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL097638V                       1366                                    THIS PART FAILED AT THE WELD THAT ATTACHES PN 12020( UNIVERSAL) TO THE LANDING GEAR SHOCK STRUT.  THIS PART IS LOCATED AT THE POINT WHERE THE SHOCK STRUT ATTACHES TO THE LANDING GEAR TO FUSELAGE SUPPORT TUBE AT THE FRONT OF THE RT WING MAIN SPAR.  THIS PART FAILED DURING A NORMAL TAKEOFF.  THE PART BROKE AT THE WELD BREAKING THE WELD ON ONE SIDE.  THE WELD  DID NOT APPEAR TO HAVE COMPLETE PENETRATION.  INTERNAL CORROSION MAY HAVE BEE A FACTOR.  THIS PART APPEARS TO BE THE WEAKEST PART OF THE ENTIRE SHOCK STRUT SYSTEM.  I WOULD RECOMMEND THAT THIS PART BE MADE OF THICKER MATERIAL UTILIZING A MORE EXTENSIVE WELD WITH GOOD PENETRATION.  (K)                                                                           1L71 3O3  O  A758    E14EA                
20070109000032007010900003CE  2007       1          9          2006FA0001204    120061118G323012838002115     RELEASE CABLE                           BEECH MU300 400A        1155402CE  PWA   JT15  JT15D5      52112NE                              LT MLG          FRAYED          B  E81RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL0395GK 7502                   RK27                                    DURING SCHEDULE (A) AND (B) INSPECTION FOUND LT MLG EMERGENCY UPLOCK RELEASE CABLE ASSY.  SEVERLY FRAYED AND CABLE FUNCTION COMPROMISED AT UPLOCK ATTACH CLEVIS END.  THIS SB 32-3200.  SB 32-3200 IS A RECOMMENDED SB ONLY, COMPLIANCE RECOMMENDED WHEN CABLE ASSY REPLACEMENT REQUIRED.  NO RECORD OF PREVIOUS COMPLIANCE ON THIS AIRCRAFT.  (K)                                                                                                                                                                                                                                                                                                                                                                                              2H72 4F4  FRTA16SW   E25EA                
20070122001862007012200186CE  2007       1          22         2006FA0001205    120061120G551145A21104012     RIB                                     BEECH MU300 400A        1155402CE  PWA   JT15  JT15D5      52112NE                              HORIZONTAL STAB CRACKED         B  E81RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL03311HS2142                   RK296                                   DURING AN A, B, AND C INSPECTION, FOUND THE HORIZONTAL STABILIZER MOUNTING FACES NOT PARALLEL WITH THE VERTICAL STABILIZER, HORIZONTAL STABILIZER ROLLER CLEARANCE CHECKS IAW MM 27-40-00 OUT OF SERVICE LIMITS.  INSPECTED STABILIZER IAW MFG COMMUNIQU NR 70 AND FOUND RT HORIZONTAL STABILIZER RIB, PN 45A21104012, CRACKED.  REPLACED RIB AND REINSTALLED STABILIZER, HORIZONTAL STABILIZER ROLLER CLEARANCE CHECKS NOW WITHIN SERVICE LIMITS.  IAW COMMUNIQU NR 70, ROLLER GAP DIMENSIONS OUT OF SERVICE LIMITS MAY BE CONTRIBUTING TO PROBLEM.  AFFECTED STRUCTURE HAS NOT YET BEEN INCLUDED IN SCHEDULED INSPECTIONS GUIDE.  (K)                                                                                                       2H72 4F4  FRTA16SW   E25EA                
20070116000712007011600071SO  2007       1          16         2006FA0001206    120061206G5711202394          NUT                                     AYRES S2    S2RRESTD    0970101SO  PWA   R1340 R1340*      52016NE                              WING SPAR       DAMAGED         D  PWWGO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP178960Q                       2450R                                   WHILE PERFORMING (SPLICE BLOCK) MAINTENANCE A NEW TUBE NUT HAD ITS THREADS PULLED OUT BEFORE REACHING TORQUE.  THE FOLLOW ON PART WAS EXAMINED AND WAS FOUND TO BE LOOSE ON THE BOLT, EVEN THE USED TUBE NUT WAS TIGHTER.  SUSPECT PANTS HAVE NO PN OR STAMP, ALSO NO INDENTATIONS ON FACE OF THE NUT (NOT VISIBLE WHEN INSTALLED).  ALMOST MADE TORQUE.  (K)                                                                                                                                                                                                                                                                                                                                                                                   1L71 3R3  R  A4SW    5E2                  
20070116000472007011600047SO  2007       1          16         2006FA0001207    220061122G8500                CASE                                    BEECH 35    V35         1151538CE  CONT  O520  IO520BA     17032SO                              ENGINE          DAMAGED         G      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW11205DB                       D8060       1207758A                    ENGINE LT CASE, MALT DEVELOPED HOLE APPROX 6 INCHES X 4 INCHES AS ROD-PISTON APPEARS TO BE MISSING FOR NR 4 CYLINDER.  ENGINE OPERATED:  (104 HOURS - 2004), (14 HOURS - 2005), (12 HOURS - 2006).  PROPELLER RECENTLY SHIMMED BLADE NR 3, RED DYE AROUND PROP SEAL.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L71 3O3  O  3A15    E5CE                 
20070116000572007011600057EA  2007       1          16         2006FA0001208    220061010G7320                LINE                                    PIPER PA23  PA23250     7102308SO  LYC   O540  TIO540C1A   41532EA                              ENG FUEL        LEAKING         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO016879A     2                 277954104                               FUEL LEAKING, TURBOCHARGER AIR LINE TO FUEL PUMP.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L72 3O3  O  1A10    E14EA                
20070116000482007011600048EA  2007       1          16         2006FA0001209    220061010G7310RG17980YM       LINE                                    PIPER PA23  PA23250     7102308SO  LYC   O540  TIO540C1A   41532EA                              TURBOCHARGER    LEAKING         D      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  NRNOT REPORTED   1                      SO016879A     2                 277954104                               FUEL LEAKING OUT TURBOCHARGER AIR LINE TO FUEL PUMP.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 3O3  O  1A10    E14EA                
20070116000722007011600072EA  2007       1          16         2006FA0001210    220061010G7310RG179803M       TURBOCHARGER                            PIPER PA23  PA23250     7102308SO  LYC   O540  TIO540C1A   41532EA                              LT ENGINE       LEAKING         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO016879A     2                 277954104                               FUEL LEAKING OUT TURBOCHARGER AIR LINE TO FUEL PUMP.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 3O3  O  1A10    E14EA                
20070116000632007011600063EA  2007       1          16         2006FA0001211    220061010G7310RG17980JM       LINE                                    PIPER PA23  PA23250     7102308SO  LYC   O540  TIO540C1A   41532EA                              FUEL SYSTEM     LEAKING         D      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  NRNOT REPORTED   1                      SO016879A     2                 277954104                               FUEL LEAKING OUT TURBOCHARGER AIR LINE TO FUEL PUMP.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 3O3  O  1A10    E14EA                
20070116000762007011600076CE  2007       1          16         2006FA0001212    120061122G552050524414        BELLCRANK                               BEECH 80    65B80       1152812CE  LYC   O720  IO720A1B    41546EA                              RT ELEVATOR     CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP1344MA                        LD412       L15595YA                    A CRACK WAS FOUND ON THE RT BELLCRANK SUPPORT ASSY.  DURING A MANDITORY 5 YEAR INSPECTION IAW MSB 2231 REV 1. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L72 3O3  O  3A20    1E15                 
20070104000612007010400061CE  2007       1          4          2006FA0001213    120060407G8011PM2401H         STARTER                                 CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              ENGINE          FAILED          G      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP056564723                     172S9778                                STARTER WOULD NOT STAY ENGAGED.  STARTER ONLY HAS 23.4 HR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1H71 3O3  ONT3A12    1E10                 
20070108001532007010800153CE  2007       1          8          2006FA0001214    120061221G8011PM2401          STARTER                                 CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              ENGINE          STUCK           G      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP05                            172S9778                                STARTER STUCK IN ENGAGED MODE                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3O3  ONT3A12    1E10                 
20070108001542007010800154CE  2007       1          8          2006FA0001215    120060306G8011PM2401          STARTER                                 CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              ENGINE          SPINNING        G      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP05259TA1585                   172S9225                                STARTER WILL NOT STAY ENGAGED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H71 3O3  ONT3A12    1E10                 
20070108001552007010800155CE  2007       1          8          2006FA0001216    120061221G8011PM2401          STARTER                                 CESSNA172   172S        2072439CE                                                               ENGINE          MALFUNCTIONED   G  GBMSO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP05879LB289                    172S9879                                STARTER SPINS BUT WILL NOT ENGAGE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O    NT3A12                         
20070108001622007010800162CE  2007       1          8          2006FA0001217    120060810G8011PM2401H         STARTER                                 CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              ENGINE          SPINNING        G  GBMSO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP0565647240                    172S9778                                STARTER FAIL, WOULD NOT ENGAGED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1H71 3O3  ONT3A12    1E10                 
20070108001632007010800163CE  2007       1          8          2006FA0001218    120061207G8011PM2401H         STARTER                                 CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              ENGINE          SPINNING        G  GBMSO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP0565647146                    172S9778                                STARTER WOULD NOT ENGAGED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1H71 3O3  ONT3A12    1E10                 
20070108001772007010800177CE  2007       1          8          2006FA0001219    120061221G8011                STARTER                                 CESSNA172   172S        2072439CE                                                               ENGINE          MALFUNCTIONED   G  GBMSO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP05879LB231                    172S9879                                STARTER WOULD NOT ENGAGE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3O    NT3A12                         
20070108001802007010800180CE  2007       1          8          2006FA0001220    120061020G8011PM2401          STARTER                                 CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              ENGINE          SPINNING        G  GBMSK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP05259TA68                     172S9225                                STARTER SPINS BUT WILL NOT ENGAGE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O3  ONT3A12    1E10                 
20070108001812007010800181CE  2007       1          8          2006FA0001221    120060909G8011PM2401          STARTER                                 CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              ENGINE          SPINNING        G      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP05259TA142                    172S9225                                STARTER SPINS BUT WILL NOT ENGAGE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O3  ONT3A12    1E10                 
20070108001822007010800182CE  2007       1          8          2006FA0001222    120061221G8011PM2401          STARTER                                 CESSNA182   182T        2072703CE  LYC   O540  IO540*      41532EA                              ENGINE          MALFUNCTIONED   G      K   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      WP052019V269                    18281699                                STARTER STUCK IN ENGAGED MODE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H71 3O3  ONT3A13    1E4                  
20070108001852007010800185CE  2007       1          8          2006FA0001223    120061221G8011PM2401          STARTER                                 CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              ENGINE          FAILED          G      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP05259TA126                    172S9225                                STARTER BENDIX FAILED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3O3  ONT3A12    1E10                 
20070109000412007010900041CE  2007       1          9          2006FA0001225    120061003G8011PM2401H         STARTER                                 CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              ENGINE          SPINNING        G      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP0565647115                    172S9778                                STARTER WOULD NOT ENGAGED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1H71 3O3  ONT3A12    1E10                 
20070109000592007010900059CE  2007       1          9          2006FA0001226    120060924G8011PM2401          STARTER                                 CESSNA172   172S        2072439CE                                                               ENGINE          LOCKED          G  GBMSK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP05658311157                   172S9796                                STARTER STUCK ENGAGED AND LOCKED PROP.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3O    NT3A12                         
20070109000602007010900060CE  2007       1          9          2006FA0001227    120061212G8011PM2401H         STARTER                                 CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              ENGINE          SPINNING        G      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP056564711                     172S9778                                STARTER WOULD NOT ENGAGED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1H71 3O3  ONT3A12    1E10                 
20070118000392007011800039GL  2007       1          18         2006FA0001228    320061222G6110D68315A         CLAMP                                                                                                       HARTZLHCA2  HCA2MVK2    GL  PROPELLER BLADE CRACKED         C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO19                                                    H632            DURING A ROUTINE PRE-FLIGHT INSPECTION OF PROPELLER ASSY, A CRACK WAS IDENTIFIED ON BLADE CLAMP PN D-6831-5A, REV K, SN 3194A.  PROP WAS REMOVED FROM AC FOR FURTHER INSPECTION.  INSPECTION CONFIRMED OPERATOR IDENTIFIED DEFECT AND PART FORWARDED FOR FURTHER EVALUATION.  THIS PART IS A TERMINATING ACTION FOR AD NOTE 97-18-02.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                   5  CP24EA    
20070118001312007011800131SO  2007       1          18         2006FA0001229    220061122G8550LPMILH50555     LINE                                    BEECH 35    V35         1151538CE  CONT  O520  IO520BA     17032SO                              ENGINE OIL      BROKEN          G      O   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      SW11205DB                       D8060       1207758A                    STARFLEX 193, LOW PRESSURE HOSE, LP MIL-H-50555 WAS USED TO CONNECT OIL COOLER TO FIREWALL FITTING.  OIL PRESSURE WILL RUN BETWEEN 50-100 PSI IN LINE.  HOSE BROKE AT FITTING AT OIL COOLER OUTLET,  ALL OIL WAS PUMPED OUT OF ENGINE CAUSING ROD TO BE RAMMED THROUGH LT CASE HALF. (NORMAL TSO AS1072 HOSE IS INSTALLED IN THIS POSITION.  STARFLEX 2650).  (K)                                                                                                                                                                                                                                                                                                                                                                               1L71 3O3  O  3A15    E5CE                 
20070116000662007011600066CE  2007       1          16         2006FA0001230    120061214G2497501122804       WIRE                                    LEAR  35    35A         5170602CE                                                                               MISINSTALLED    B  JGVRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE09421SV                       660                                     CELL DIP SWITCH INSTALLED 180 DEGREES OUT.  CELL WIRING MISROUTED AND IMPROPER GAUGE WIRE.  MULTIPLE COLD CRACKED SOLDER JOINTS BROKEN AND POORLY REPAIRED TRACES.  BATTERY T3 AND P3 ARE BROKEN.  UNIT SENT BACK, AS CORE SEEMS TO BE A WORKMANSHIP ISSUE. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F      A10CE                        
20070118001332007011800133CE  2007       1          18         2006FA0001231    120061130G3411E420191         STATIC PORT                             RAYTHNDH125 DH125       4230106CE  GARRTTTFE731TFE731*     01518WP                              FUSELAGE        MISINSTALLED    B  JGVRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE07700VT                       257158                                  ROSEMOUNT STATIC PORTS DO NOT FIT CONTOUR OF AIRCRAFT SKIN. PORTS ARE NOT UNIFORM IN THICKNESS.  CAN NOT INSTALL NEW PORT AND MATCH STEP HEIGHT TO MEET ORIGINAL RVSM CERTIFICATION.  OTHER ISSUES: WHEN PORT IS INSTALLED, PORT CAUSE STRESS.  AC SKIN DO TO CONTOUR FIT.  INSTALLATION OF PORT ALSO PUTS STRESS ON PLATE TO HEATER BLOCK AND CAUSES CRACKING IN THE MATING SURFACE CAUSING PORT TO HAVE STATIC SYSTEM LEAK.  (K)                                                                                                                                                                                                                                                                                                              2L72 4J4  FRTA3EU    E6WE                 
20070111001462007011100146CE  2007       1          11         2006FA0001233    120061209G2497AE776L845       CONNECTOR                               CESSNA750   750         2076810CE  ALLSN AE3007AE3007C          GL                              MAIN BATTERY    SHORTED         B  CNQRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CE07913QS6798                   7500113                                 BATTERY OVERTEMP INDICATED R-RED CAS MESSAGE IN FLIGHT.  FOUND SPLICE AT THE BATTERY TEMP SENSOR CONNECTOR PY044 BROKEN.  ALSO CONNECTOR WAS FOUND BADLY CORRODED INSIDE OF CONNECTOR.  REPLACED CONNECTOR PY044 AND REPLACED WIRES IAW CE750 WIRING MANUAL 20-10-06.  THE INCIDENT WAS AN INDICATION PROBLEM ONLY AND BOTH AIRCRAFT BATTERIES WERE FOUND TO BE NORMAL (AIRWORTHY) WITH NO ACTION REQUIRED.  (K)                                                                                                                                                                                                                                                                                                                                2L72 4J4  FRTT00007WITE6CH                
20070118000722007011800072EA  2007       1          18         2006FA0001234    220061202G8520                PISTON                                  CESSNA150   152         2071835CE  LYC   O235  O235N2C     41505EA                              NR 3 CYLINDER   STUCK           D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL11942868774 1762              15285639    L2404715                    ENGINE QUIT IN FLIGHT, FOUND NR 3 CYLINDER PISTON NOT MOVING IN CYLINDER WHEN TURNING PROP.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1H71 3O3  ONT3A19    E223                 
20070109000102007010900010EA  2007       1          9          2006FA0001235    220061227G8530LW19001         VALVE GUIDE                             CESSNA182   182T        2072703CE  LYC   O540  IO540AB1A5       EA                                              STUCK           D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL0719HP 1300 200               18281266    L2895948B                   PERFORMED COMPRESSION CHECK ON ENGINE AND HAD 5/80 PSI ON NR 6 CYL, STAKED EXHAUST VALVE AND GOT 78/80. PERFORMED SB 388C AND HAD TO REAM VALVE GUIDES TO GET WITH-IN LIMITS OF SB.  IT WAS ONLY 200 HRS SINCE LAST SB COMPLIANCE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O3  ONT3A13    1E4                  
20060914001682006091400168    2006       9          14         2006FAA0901      420060906G2210841341          AUTOPILOT SYS                           PIPER PA46  PA46500TP   7104622SO  PWA   PT6   PT6*        52043EA                                              BURNED OUT      B      K   NONE                                                                                            B  SMOKE/FUMES/ODORS/SPARKS                                                      NRNOT REPORTED   1                      SW4271562                       4697081                                 THE COMPLAINANT NOTED SMOKE IN THE COCKPIT.THE SOURCE OF THE SMOKE WAS THE FAILURE OF A FILTER CAPACITOR, C20 (P/N 1131013-106035,) ON THE POWER SUPPLY BOARD (P/N 71115-05.) IT HAD BURNED OUT CAUSING THE SMOKE.  IT IS A FILTER CAPACITOR FOR THE -15V SIDE OF THE DC TO DC CONVERTER.  THE PART WAS INSTALLED CORRECTLY (POLARITY), AND NONE OF THE SURROUNDING DEVICES WERE ABNORMAL.  IT WAS A PART THAT HAS HISTORICALLY GIVEN US THIS TYPE OF FAILURE, ALTHOUGH WEVE NEVER HAD ISSUE WITH THE PART LOCATED HERE.  IT APPEARS TO BE A ONE TIME DEFECTIVE DEVICE.                                                                                                                                                                        1L71 3O3  TRTA25SO   E2NE                 
20070125001392007012500139NE  2007       1          25         2007FA0000000    220061201G7200                ENGINE                                  CNDAIRCL600 CL6002A12   1900304EA  GE    CF34  CF341A           NE                              RIGHT           FAILED          Z      C   ABORTED TAKEOFF                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  TOTAKEOFF        1                      WP01388DB6080 380               3016        350152                      RT ENGINE FAILURE AT T/O. ALL INDICATIONS WERE NORMAL ON ENGINE START AND TAXI. UPON THRUST ADVANCEMENT FOR TAKEOFF, AT APPROXIMATELY 60 PERCENT N1 WE HEARD AND FELT A COMPRESSOR STALL. THE THRUST LEVER WAS IMMEDIATELY RETARDED TO IDLE AND TEMPERATURES WERE NOTED TO BE IN THE RED(APPROX 950 DEGREESC). WE SHUT DOWN THE ENGINE AND OBSERVED THE TEMPERATURES REMAINING IN THE RED FOR APPROXIMATELY 6 TO 8 SECONDS AFTER SHUTDOWN. WE TAXIED BACK TO BOMBARDIER AND REPORTED THIS INCIDENT. SUBSEQUENT EXAMINATION REVEALED DAMAGE IN THE FORWARD AND AFT SECTIONS OF THE ENGINE.  ENGINE REMOVED & ROUTED TO FOR REPAIR.                                                                                                               2L72 4F4  FRTA21EA   E15NE                
20070118000972007011800097EU  2007       1          18         2007FA0000002    120061206G5302                DOUBLER                                 SNIAS 350   AS350B3     8680954EU  TMECA ARRIELARRIEL2B         NE                              TAIL ROTOR      CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP01110E 1065                   3322                                    FOUND CRACKS 2 EA ON LT OUTSIDE DOUBLER ASSY.  2 RIVETS WERE POPED OUT.  DAMAGE VISIBLE ONLY AFTER REMOVAL OF TAIL ROTOR GEARBOX COWLING.  FOUND DURING 100 HR INSP.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1G71 3U3  U  H9EU    E00054EN             
20070116000672007011600067EU  2007       1          16         2007FA0000003    120061110G36001U478003        PUMP                                    GROB  120   G120A       1660208EU  LYC   O540  AEIO540*         EA                              ENGINE          OUT OF LIMITS   B  VJ3RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP07864AF52                     85004                                   PILOT REPORTED SUCTION INDICATOR WAS BELOW LIMITS, AC RETURNE TO BASE.  UPON TROUBLESHOOTING, THE MECHANIC REMOVED THE AIR PUMP AND NOTICED THE SHAFT WAS VERY EASY TO ROTATE, HAD NO RESISTANCE TO IT.  NO PROBABLE CAUSE OR RECOMMENDATIONS AT THIS TIME.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L71 3O3  ORTA49CE   1E4                  
20070118000362007011800036EU  2007       1          18         2007FA0000004    120061026G37101U478           PUMP                                    GROB  120   G120A       1660208EU  LYC   O540  AEIO540D4D5      EA                              VACUUM SYS      WEAK            B  VJ3RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP07864AF                       85004       RL2802548                   IN FLIGHT, THE INSTRUMENT VACUUM SYSTEM WOULD NOT PUT OUT PROPER SUCTION AND CAUSED THE ATTITUDE INDICATOR TO TUMBLE.  THE AC RETURNED TO MAINTENANCE AND AN INSPECTION OF THE SYSTEM  FOUND THAT THE PUMP WAS WEAK.  PUMP WAS REMOVED AND A NEW PUMP INSTALLED.  OPERATIONAL CHECK OF THE SYSTEM CHECKED NORMAL.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                          1L71 3O3  ORTA49CE   1E4                  
20070116000732007011600073EU  2007       1          16         2007FA0000005    120060922G37001U478           PUMP                                    GROB  120   G120A       1660208EU  LYC   O540  AEIO540*         EA                              VACUUM SYSTEM   WORN            B  VJ3RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP07862AF                       85002       RL2515648A                  DURING FLIGHT SUCTION PRESSURE READING DROPPED TO ZERO, DURING FURTHER TROUBLESHOOTING TECHICIAN FOUND THE ENGINE DRIVEN DRY AIR PUMP SHAFT HAD BROKEN.  PROBABLE CAUSE COULD BE FROM ENGINE VIBRATION OR  POOR PARTS.  RECOMMENDATION AT THIS TIME IS FOR THE MFG TO INVESTIGATE WHY PUMP IS FAILING SO EARLY.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                            1L71 3O3  ORTA49CE   1E4                  
20070116000112007011600011EU  2007       1          16         2007FA0000006    120060926G37001U478           SHAFT                                   GROB  120   G120A       1660208EU  LYC   O540  AEIO540*         EA                              AIR PUMP        BROKEN          B  VJ3RO   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      WP07865AF194                    85005                                   DURING ENGINE START, SUCTION PRESSURE WAS READING ZERO, DURING FURTHER TROUBLESHOOTING, TECH FOUND THE ENGINE DRIVEN DRIVEN DRY AIR PUMP HAD A BROKEN SHAFT.  PROBABLE CAUSE COULD BE FROM VIBRATION OR HARD START.  NO RECOMMENDATION AT THIS TIME.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L71 3O3  ORTA49CE   1E4                  
20070125001102007012500110EU  2007       1          25         2007FA0000007    120061030G37101U478           PUMP                                    GROB  120   G120A       1660208EU  LYC   O540  AEIO540*         EA                              VACUUM SYS      WORN            C  VJ3RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP07865AF109                    85005                                   DURING FLIGHT SUCTION PRESSURE READING DROPPED TO ZERO, DURING FURTHER TROUBLESHOOTING, TECH FOUND THE ENGINE DRIVEN AIR PUMP WAS NOT PRODUCTING ENOUGH SUCTION.  PROBABLE CAUSE COULD BE FROM PISTION WEARING INSIDE OF PUMP.  RECOMMENDATION AT THIS TIME IS FOR THE MFG TO INVESTIGATE WHY PUMP PISTON IS FAILING.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                      1L71 3O3  ORTA49CE   1E4                  
20070109000022007010900002SO  2007       1          9          2007FA0000008    120061214G57116207006         SPAR                                    PIPER PA28  PA28140     7102802SO  LYC   O320  O320*       41508EA                              LT MLG          LOOSE           B  A5ORO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO09157153501                   287325144                               DURING AN ANNUAL INSPECTION OF THE LT MAIN LANDING GEAR ASSY PN 35644-902, IT WAS FOUND TO BE LOOSE IN THE MAIN WING SPAR.  THE LT MAIN LANDING GEAR WAS REMOVED FOR FURTHER INSPECTION OF THE LT MAIN WING SPAR ASSY GEAR ATTACHING BOLT HOSES AND ATTACH POINTS.  CLOSE INSPECTION FO THE WING SPAR SHOWED THAT THE LOWER (4) BOLT HOLES HAD BEEN ELONGATED.  IT APPEARED THAT ALL BOLTS WERE TIGHT AND THIS CONDITION HAD BEE LOOSE FOR SOME TIME.  RECOMMEND CLOSE INSPECTION OF LANDING GEAR ATTACH POINTS DURING ALL INSPECTIONS.  (K)                                                                                                                                                                                                    1L71 3O3  O  2A13    E274                 
20070111001372007011100137GL  2007       1          11         2007FA0000009    120061218G8011642083          DRIVE ASSY                              CIRRUSSR    SR22        2130001GL  CONT  O550  IO550N      17042SO                              STARTER         CRACKED         B  LC1RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA07249CK                       0766        9117066                     STARTER DRIVE WAS REMOVED FROM AIRCRAFT DUE TO SLIPPING.  INSPECTION AFTER REMOVAL FOUND A CRACK EMANATING FROM THE STUD BOSS LOCATED AT APPROXIMATELY THE 7:00 POSITION.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L71 3O3  ONTA00009CHE3SO                 
20070111001382007011100138    2007       1          11         2007FA0000010    420061218G2562                BATTERY                                 CIRRUSSR    SR22        2130001GL  CONT  O550  IO550*           SO                              ELT             LEAKING         D      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      WP11910JR           040334      0142                                    DURING ANNUAL INSPECTION, FOUND BATTERY COMPARTMENT CONTAMINATED BY LEAKAGE FROM D CELLS AND BATTERY TERMINALS CORRODED.  BATTERIES FOUND DEAD.  BATTERIES WERE INSTALLED MARCH 2004 AND HAVE A EXPIRATION DATE OF MARCH 2008.  THE MODEL ELT IS CERTIFIED BY THE MFG TO USE THE BATTERY EXPIRATION DATES FOR SERVICE RATHER THAN A LIMITED CALENDAR TIME SUCH AS THE TYPICAL 24 MONTHS.  THIS INSPECTOR HAS RECENTLY FOUND OTHER ELTS OF THE SAME TYPE IN THE SAME CONDITION.  RECOMMENDATION THA THE SERVICE LIFE OF THE BATTERIES BE LIMITED TO 24 MONTHS.  (K)                                                                                                                                                                              1L71 3O3  ONTA00009CHE3SO                 
20070116000622007011600062WP  2007       1          16         2007FA0000011    220060929G725030606852        RETAINER                                LEAR  45    45LEAR      5170805CE  GARRTTTFE731TFE731*     01518WP                              LPT 2           CORRODED        F      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP07VH5QR4660                   45195       P111119C                    MATERIAL LOSS ON THE LPT2 NOZZLE RETAINER WITH DISLODGED PINS THAT LIKELY LED TO DOWN STREAM LPT3 BLADE MID SPAN FRACTURES AND DISPLACED MATERIAL IN THE FORM OF IMPACT DAMAGE.  THIS ENGINE WAS PRESERVICE  BULLETIN 72-5165 AND ADDRESSES THIS ISSUE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F4  FRTT00008WIE6WE                 
20070118001292007011800129    2007       1          18         2007FA0000012    420061220G256457FASA2321325   LIFE RAFT                               ISRAELGALAXYGALAXY      4500307EU                                                               CABIN           MISRIGGED       B  JG1RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA25889G                        046                                     THIS RAFT WAS INSTALLED ON AC BUT MAY BE INSTALLED ON OTHER SIMILAR AC.  MOORING THE LINE (FIRING LINE) WAS FOUND RIGGED WRONG.  LINE WAS TIED TO LIFE RAFT FIRST AND THEN TO THE PULL CABLE.  THE LINE SHOULD BE TIED TO THE PULL CABLE FIRST AND THEN TO THE LIFE RAFT.  RIGGED THIS WAY THE LIFE RAFT WOULD NOT DEPLOY BECAUSE THE PULL CABLE WOULD NOT BE ABLE TO BE FIRED.  (K)                                                                                                                                                                                                                                                                                                                                                            2L72 4F    RTA53NM                        
20070111001442007011100144    2007       1          11         2007FA0000013    420061220G256457FASA2321315   LIFE RAFT                               ISRAELGALAXYGALAXY      4500307EU                                                                               MISRIGGED       B  JG1RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA25889G                        046                                     THIS RAFT WAS INSTALLED ON AC BUT MAY BE INSTALLED ON OTHER SIMILAR AC.  MOOORING LINE (FIRING LINE) WAS FOUND RIGGED WRONG.  LINE WAS TIED TO THE RAFT FIRST AND THEN TO PULL CABLE.  THE LINE SHOULD BE TIED TO THE PULL CABLE FIRST AND THEN TO THE LIFE RAFT.  RIGGED THIS WAY THE LIFE RAFT WOULD NOT DEPLOY BECAUSE THE PULL CABLE WOULD NOT BE ABLE TO BE FIRED.  (K)                                                                                                                                                                                                                                                                                                                                                                    2L72 4F    RTA53NM                        
20070111001452007011100145    2007       1          11         2007FA0000014    420061220G256457FASA2321315   LIFE RAFT                               ISRAELGALAXYGALAXY      4500307EU                                                                               MISRIGGED       B  JG1RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA25889G                        046                                     THIS RAFT WAS INSTALLED ON AC BUT MAY BE INSTALLED ON OTHER SIMILAR AC.  MOORING LINE (FIRING LINE) WAS FOUND RIGGED WRONG.  LINE WAS TIED TO LIFE RAFT FIRST AND THEN TO THE PULL CABLE.  THE LINE SHOULD BE TIED TO THE PULL CABLE FIRST AND THEN TO THE LIFE RAFT.  RIGGED THIS WAY THE LIFE RAFT WOULD NOT DEPLOY BECAUSE THE PULL CABLE WOULD NOT BE ABLE TO BE FIRED.  (K)                                                                                                                                                                                                                                                                                                                                                                2L72 4F    RTA53NM                        
20070116000562007011600056    2007       1          16         2007FA0000015    120061214G35004357B           VALVE                                                                                                                                   OXYGEN SYS      LEAKING         B  WP1RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW15                                                                    OXYGEN VALVE HAD A FUNCTIONAL TEST, ON 06/07/2006.  THE WORK WAS ACCOMPLISHED ON WO 06-5301.  THIS COMPONENT LEAKED OXYGEN WHEN INSTALLED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           
20070118000782007011800078    2007       1          18         2007FA0000016    120061214G35004357B           VALVE                                                                                                                                   OXYGEN SYSTEM   LEAKING         B      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW15WP1R                                                                OXYGEN VALVE HAD A FUNCTIONAL TEST ON 09/25/2006.  THE WORK WAS ACCOMPLISHED ON WO 06-5970.  THIS COMPONENT LEAKED OXYGEN WHEN INSTALLED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            
20070118000922007011800092    2007       1          18         2007FA0000019    120061214G350029909256B       VALVE                                                                                                                                   OXYGEN SYSTEM   LEAKING         B  WP1RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW15                                                                    OXYGEN VALVE HAD A FUNCTIONAL TEST ON 06/07/2006.  THE WORK WAS ACCOMPLISHED ON WO 06-5775.  THIS COMPONENT LEAKED OXYGEN WHEN INSTALLED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            
20070118001252007011800125    2007       1          18         2007FA0000020    120061214G35004357B           VALVE                                                                                                                                   OXYGEN SYSTEM   LEAKING         B  WP1RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW15                                                                    OXYGEN VALVE WAS INSPECTED ON 10/09/2006.  THE WORK WAS ACCOMPLISHED ON WO 066023.  THIS COMPONENT LEAKED OXYGEN WHEN INSTALLED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     
20070116000342007011600034EU  2007       1          16         2007FA0000021    120061127G5100                PIN                                     AIRBUSA340  A340*              EU                                                                               MISMANUFACTURED B  VS6YO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA35                            VARIOUS                                 TWO OCCURRENCES OF A RETAINING PIN HOLDING THE UNIVERSAL-JOINT TOGETHER, HAVING INSUFFICIENT PEENING TO RETAIN THE PIN, HAS BEEN IDENTIFIED IN BUILD OF THE UNIT BY THE ACTUATOR/DRIVE SHAFT MFG.  THE PIN IS THEREFORE NOT SUFFICIENTLY RETAINED AND MAY WALK OUT OF THE UNIVERSAL JOINT UNDER ACTUATION LOADS.  THREE POTENTIALLY HAZARDOUS CONDITIONS HAVE BEEN IDENTIFIED.  1) THERE WILL BE A NR OF METAL PARTS FREE IN THE FUEL TANK- LIGHTNING STRIKE.  2) THE JOINT WILL FAIL AND PREVENT TRANSMISSION OF DRIVE THROUGH THE SHAFT TO THE ACTUATED VALVE.  THE ACTUATED VALVE WILL FAIL TO OPERATE, BUT A POSITIVE ACTUATION WILL BE INDICATED TO THE FLIGHT CREW.  MONITORING OF THE FUEL CONTENTS WILL BE REQUIRED TO VERIFY THAT THE C2L74 4F    RTA197                         
20070118000952007011800095SW  2007       1          18         2007FA0000024    120061130G5520F3114           BEARING                                 MOONEYM20   M20G        5870316SW  LYC   O360  O360A1D     41514EA  HARTZLHCC2Y HCC2YK1     GL  ELEVATOR ROD ENDFROZEN          B  DPPRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP25684MA                       680005      RL2292836A                  ELEVATOR PUSH ROD END BEARING (PHF31-14, FOUND TO BE FROZEN FROM RUST AND GRIME.  ROD END BEARING BROKE AT THREADED PORTION DUE TO LACK OF MOVEMENT.  AD 73-21-01 ADDRESSES LUBRICATION OF ALL CONTROL AND LANDING GEAR ROD END BEARINGS BUT DOES NOT ADDRESS INSPECTION OF OPERATION AND FREEDOM OF MOVEMENT.  SERVICE INSTRUCTION M20-106 GIVES A GOOD INSPECTION OF PRIMARY FLIGHT CONTROL/ JOINTS.  THAT SHOULD BE INCORPORATED INTO THE INSPECTION MANUAL AND/OR AD.  (K)                                                                                                                                                                                                                                                                  1L71 3O3  O  2A3     E286    5  CP920     
20070116000532007011600053CE  2007       1          16         2007FA0000025    120060725G251007140593        SEAT BACK                               CESSNA172   172N        2072434CE  LYC   O320  O320*       41508EA                              COCKPIT         BROKEN          B  BIIRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA21733BE4070                   17268161                                INSPECTED SEATS IAW AD 87-20-03R2 FOUND PILOTS SEAT BOTTOM ASSY BROKEN AT LEFT FWD ATTACH POINT AND RT FWD CRACKED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1H71 3O3  ONT3A12    E274                 
20070111001392007011100139SO  2007       1          11         2007FA0000026    120061211G8011MZ6222          STARTER                                 PIPER PA28  PA28161     7102803SO  LYC   O320  O320D3G     41508EA                              ENGINE          BROKEN          B  BIIRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA219089N600                    2816003     L1624939A                   WHEN STARTING AIRCRAFT, MADE LOUD NOISE AT STARTER.  INSPECTED AND FOUND BENDIX SHATTERED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L71 3O3  O  2A13    E274                 
20070112000022007011200002EA  2007       1          12         2007FA0000027    220061204G8530                PISTON                                  CESSNA150   152         2071835CE  LYC   O235  O235N2C     41505EA  MCAULY1A103 1A103TCM    GL  NR 3 CYLINDER   INOPERATIVE     D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL11942861762                   15285639    L2404715    VH43067         NR 3 CYLINDER PISTON DOES NOT MOVE IN CYLINDER WHEN YOU TURN PROPELLER.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H71 3O3  ONT3A19    E223    5  NP50GL    
20070111001412007011100141SO  2007       1          11         2007FA0000028    220061229G85506566161         DIPSTICK                                AMTR  LANCARLC41550FG   5150001GL  CONT  O550  TSIO550C         SO                              ENGINE          SEPARATED       B      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA21442TA189                    41532       802791                      THE OIL GAGE ASSEMBLY (DIPSTICK) SEPARATED AT THE UPPER SWEDGED JOINT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L71 3O3  ORTEXPA1L71E5SO                 
20070111001402007011100140SO  2007       1          11         2007FA0000029    120061219G3210AN411A          BOLT                                    PIPER PA28  PA28161     7102803SO  LYC   O320  O320D3G     41508EA  SNSNCH70C   70CM6       EA  MLG             CORRODED        D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO158156T8236                   288016219   L9820394    A549B2          WHILE WASHING AC, SCRUB BRUSH NOCKED OFF NUT AND ENGAGED PORTION OF ONE OF THE (AN4-11A) BOLTS THAT SECURES THE RT MLG ASSY TO THE RT WING.  BOLT WAS CORRODED ALL THE WAY ACROSS ITS CROSS SECTION.  SUGGESTIONS: PERIODICALLY CHECK TORQUE ON THESE BOLTS TO ENSURE BOLT NOT CORRODED THROUGH LIKE THIS ONE.  REPLACE THES BOLTS PERIODICALLY TO PRECLUDE CORROSION FAILURE.  (K)                                                                                                                                                                                                                                                                                                                                                             1L71 3O3  O  2A13    E274    5  NP28NE    
20070111001342007011100134CE  2007       1          11         2007FA0000030    120061215G214083D59           VALVE           JANITROL                BEECH 95    95B55       1152729CE  CONT  O470  IO470*      17026SO                              CABIN HEATER    FAILED          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NE033845L                       TC2378                                  FOUND THERMOSTAT WORKING, BUT FUEL SOLENOID NOT STOPPING FUEL DELIVERY EVEN WITH POWER TO VALVE DISTUPTED.  CABIN HEATER ONLY SHUTDOWN WHEN OVERHEAT SWITCH OPENED.  VALVE INFO:  MODEL NR 4400B.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L72 3O3  ORT3A16    E1CE                 
20070125001992007012500199CE  2007       1          25         2007FA0000033    120061219G8011MZ4220          STARTER                                 BEECH 76    76          1153005CE  LYC   O360  O360A1G6D        EA                              ENGINE          INTERMITTENT    B  BIIRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA216015639                     ME147       L56171A                     REPEATED TRYS, BENDIX FAILED TO ENGAGE.  LUBRICATED AND INSPECTED BENDIX, FAILS TO ENGAGE EVERY OTHER TIME.  IT STARTS (1) TIME THEN FAILS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L72 3O3  O  A29CE   E286                 
20070125002002007012500200CE  2007       1          25         2007FA0000034    120061124G80119301001         DRIVE GEAR      LAMAR                   CESSNA172   172S        2072439CE  LYC   O360  IO360A1A    41514EA                              STARTER         FAILED          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA05856SP           85007449    172S8124                                STARTER WAS REMOVED AFTER THE DRIVE GEAR BROKE INTO PIECES AND JAMMED STARTER FROM TURNING.  COMPLETE STARTER WAS REPLACED WITH REBUILT ASSEMBLY.  SUB-PART (BENDIX DRIVE) IS PN 9301001.  THIS MECHANIC HAS SEEN THIS FAILURE 4 TO 5 TIMES.  BOTH 12 AND 24 VOLT UNITS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3O3  ONT3A12    1E10                 
20070125001962007012500196CE  2007       1          25         2007FA0000035    120061203G3350645402500       RHEOSTAT                                LEAR  35    36LEAR      5170601CE  GARRTTTFE731TFE731*     01518WP                              COCKPIT         SHORTED         D  ESPRO   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      CLCLIMB          1                      SO1171PG                        013                                     SOON AFTER TAKEOFF, THE CREW DETECTED A AN ELECTRICAL SMELL.  AFTER ATTEMPTING AND FAILING TO ISOLATE SOURCES.  THEY ELECTED TO RETURN TO DEPARTURE.  AIRPORT, AND LANDED UNEVENTFULLY.  THERE WAS NO EMERGENCY DECLARED.  MAINTENANCE REPLACED EL RHEOSTAT IAW MM.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F4  F  A10CE   E6WE                 
20070126000082007012600008NE  2007       1          26         2007FA0000037    220060915G72503360097050      SHAFT           CFMINT                  AIRBUS320   A320211     3930320EU  GE    CFM56 CFM565A     13802NE                              LP TURBINE      SEIZED          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO19SUPBD           55X31147                                            ENGINE WAS REMOVED FROM AC, ENG POSITION 1 FOR A SUSPECTED LPT SHAFT FAILURE.  ENG FAILED ON 9/15/2006 AND WAS REMOVED ON 12/3/2006.  ENG WAS INPUT ON 1/2/2007 FOR DISASSEMBLY.  ON RECEIPT OF ENG, IT WAS NOT POSSIBLE TO CARRY OUT A BORESCOPE INSP OF CORE AS IT WAS SEIZED AND WAS UNABLE TO ROTATE.  ON ROTATION OF FAN LPC SYSTEM IT WAS FOUND THAT LPT SYSTEM WAS NOT ROTATING.  DUE TO EXTENT OF DEBRIS FOUND IN LPT FROM FAILED LPT ROTOR BLADES AND VANES, IT WAS ALSO NOT POSSIBLE TO ROTATE IT INDEPENDENTLY.  ENG HAD SUFFERED MAJOR FAILURES ON FOLLOWING COMPONENTS:  LPT SHAFT, NR 4 BRG, CENTER VENT TUBE, HPT BLADES, LPT STAGE 1 VANES, LLPT ROTOR BLADES AND VANES ALL STAGES.  FURTHER DISASSEMBLY OF MODULES WILL EXPOSE 2L72 4F4  FRTA28NM   E29NE                
20070122000472007012200047    2007       1          22         2007FA0000044    420061109G3417702490031304    ADC                                     LEAR  35    35LEAR      5170600CE  GARRTTTFE731TFE73122B   01518WP                              COCKPIT         DEFECTIVE       B  BSYRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL071140A                       35045                                   DURING PREFLIGHT THE PILOTS ALTIMETER WAS FLAGGED.  THE ADC WAS FOUND TO BE DEFECTIVE AND REPLACED.  THE SYSTEM WAS TESTED AND INSPECTED AND FOUND TO COMPLY WITH FAR 91 AND TO REMAIN RVSM COMPLAINT.  THERE HAS BEEN ONE PRIOR FAILURE REPORTED ON THIS SYSTEM REPORTED ON 11-11-2005.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  F  A10CE   E6WE                 
20070122000482007012200048    2007       1          22         2007FA0000045    420061116G34178220839429      ADC                                     LEAR  60    60LEAR      5170707CE  PWA   305   PW305            NE                              LT AFT AVIONICS MALFUNCTIONED   B  BSYRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL07160AN                       126                                     THE FLIGHTCREW REPORTED INTERMITTENT LOSS OF ADC INFORMATION ON THE CAPTAIN`S PFD.  THE PRIMARY AIR DATA COMPUTER WAS FOUND TO BE DEFECTIVE AND WAS REPLACED.  THE SYSTEM WAS TESTED AND INSPECTED IAW MM AND WAS FOUND TO COMPLY WITH FAR 91.411, PART 43 AND RVSM ADC INSPECTIORS.  THE AIRCRAFT REMAINS RVSM COMPLAINT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA10CE   E35NE                
20070125002402007012500240NM  2007       1          25         2007FA0000053    120061128G32504I29R12         HOUSING         SARGENT                 BOEING737   737*               NM                                                               STEERING VAVLE  CRACKED         B  IU6RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NM01                1106                                                (REF NR: 213227/FXS)  BODY CRACKED IN CHECK VALVE PORT.  OVERPRESSURE/ CYCLIC STRESS, REDESIGN BODY.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F    RTA16WE                        
20070125000352007012500035CE  2007       1          25         2007FA0000055    120061212G29101114174S0102    HYDRAULIC LINE                          CESSNA182   TR182       2072735CE  LYC   O540  O540*       41532EA                              NLG             FAILED          D      O   OTHER                                                                                           K  FLUID LOSS                                                                    APAPPROACH       1                      SO035091S                       R18201503                               HYDRAULIC HOSE ON RETRACT SIDE OF NOSE GEAR ACTUATOR FAILED AS AIRCRAT WAS ON APPROACH AND GEARDOWN WAS SELECTED.  RESULTED IN AIRCRAFT MAKING AN EMERGENCY GEARUP LANDING.  AFTER AC WAS RECOVERED, INSPECTION OF HYDRAULIC SYSTEM REVEALED; TEFLON HYDRAULIC HOSE HAD COMPLETELY BLOW-OUT OF SWEDGED FITTING.  NO SIGNS OF HOSE LEAKING PRIOR TO INCIDENT.  (K)                                                                                                                                                                                                                                                                                                                                                                               1H71 3O3  O  3A13    E295                 
20070125001452007012500145SO  2007       1          25         2007FA0000060    120061228G2913HYC5005         PUMP                                    PIPER PA44  PA44180     7104402SO  LYC   O360  O360E1A6    41514EA                              HYDRAULIC SYS   INOPERATIVE     D      K   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      WP172PW                         447995087   L10677T                     UPON EXAMINATION OF THE AIRCRAFT IN QUESTION ON THE RUNWAY (AIRPORT MANAGER) TO TAKE PHOTOS OF THE INTERIOR OF THE AIRCRAFT SO AS TO RECORD THE POSITIONS OF ENGINE, GEAR AND CIRCUIT BREAKERS.  PIC SO THEY COULD BE RECORDED BEFORE BEING REPOSITIONED FOR SAFETY PURPOSES.  AFTER THAT WAS DONE, THE EMERGENCY GEAR KNOB AND PULLED THE LANDING GEAR HYDRAULIC CB.  THE AC WAS THEN HOISTED UP BY CRANE AND SLING AND THE GEAR CAME DOWN.  WHILE THE AC WAS HOISTED, EXAMINED THE LAND GEAR DOWN LOCKS.  ALL (3) WERE IN THE (DOWN AND LOCKED) POSITION. THE AC WAS THEN TOWED TO OUR HANGER WITHOUT ANY PROBLEMS.  JACKED UP AC AND REPOSITIONED THE CONTROLS FOR A RETRACT TEST OF THE LANDING GEAR.  UPON S3WITCHING BATTERY POWER TO (ON)1L72 3O3  O  A19S0   E286                 
20070125001302007012500130    2007       1          25         2007FA0000061    120061228G8011ES6462751       STARTER                                                                                                                                 ENGINE          LEAKING         B  WS9RK   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      NM07     2                                                              STARTER LEAKING OUT OF REAR OF STARTER PLATE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        
20070125003412007012500341NE  2007       1          25         2007FA0000062    220061004G725030606852        RETAINER                                ISRAEL1125  ASTRASPX    4500205EU  GARRTTTFE731TFE73140    29001NE                              TURBINE         SEPARATED       D      O   OTHER                                                                                           A  FLAME/FIRE                                                                    TXTAXI/GRND HDL  1                      WP071125S2445                   134         P113218                     ON 10/4/2006, 4TH AIRCRAFT EXPERIENCED A LT ENGINE EXHAUST FIRE AFTER ENGINE START AND PRIOR TO DEPARTURE.  ENGINE WAS REMOVED AND RETURNED TO MFG FOR REPAIR.  ENGINE WAS DISASSEMBLED IAW LMM 72-03-06, REV 8 FOR ENGINEERING INVESTIGATION.  DISASSEMBLY FINDINGS REVEALED PINS SECURING THE DEFLECTOR SHROUD TO THE RETAINER RING OF THE LPT2 STAGE NOZZLE RETAINER BECAME DISLODGED AND EXHIBITED CONTACT FRETTING WITH MATERIAL LOSS ON THE OUTER RETAINER.  THE ENGINE FIRE MAY HAVE RESULTED FROM THE LPT2 STAGE RETAINER PINS DISLODGING WHICH MAY HAVE LOCCKED UP THE N1 ROTATING GROUP AND PREVENTED THE N1 GROUP FROM OBTAINING GROUND IDLE WITH EXCESSIVE RAW FUEL.  SB INCORPORATED IMPROVED HARDWARE AND PROVIDES INSTRUCTIONS FO2L72 4F4  FRTA16NM   E1NM                 
20070131001152007013100115    2007       1          31         2007FA0000066    420060501G23301302045100      MONITOR                                                                                                                                 CABIN           MALFUNCTIONED   B  BT7YK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA35                                                                    POTENTIAL FOR SMOKE IN THE CABIN CAUSED BY FAILURE OF ELECTRONIC COMPONENT WITHIN IFE SCREENS.  WHILE CARRYING OUT THE REPAIR OF 6.4 LCD IN ARM AND SEAT BACK UNITS, WORKSHOP TECHNICIANS NOTED DAMAGE TO A CAPACITOR (LABELED AS C100) ON THE CIRCUIT CARD ASSY (CCA) WITHIN THE LCD.  ALTHOUGH THE UNIT WAS NOT REMOVED FROM AC FOR THIS DEFECT AND THE FAILURE OF THE COMPONENT DOES NOT APPEAR TO HAVE A DETRIMENTAL AFFECT TO THE PERFORMANCE OF THE UNIT, IT IS CONSIDERED THAT THE DAMAGE TO THE CCA IS SEVERE ENOUGH TO POTENTIALLY CAUSE SMOKE IN THE CABIN.  AT THE TIME IT WAS CONSIDERED A ONE-OFF INCIDENT AND THE WHOLE CCA WAS CHANGED.  THE THE CCA PN AFFECTED 1302160-102 AND 1302160-103.  NO DETAILED CIRCUIT DIAGRAMS OF TH                                          
20070131000072007013100007    2007       1          31         2007FA0000067    420060501G23301302046100      MONITOR                                                                                                                                 CABIN           MALFUNCTIONED   B  BT7YO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA35                                                                    POTENTIAL FOR SMOKE IN THE CABIN CAUSED BY FAILURE OF ELECTRONIC COMPONENT WITHIN IFE SCREENS.  WHILE CARRYING OUT THE REPAIR OF 6.4 LCD IN ARM AND SEAT BACK UNITS, WORKSHOP TECHNICIANS NOTED DAMAGE TO A CAPACITOR (LABELED AS C100) ON THE CIRCUIT CARD ASSY (CCA) WITHIN THE LCD.  ALTHOUGH THE UNIT WAS NOT REMOVED FROM AC FOR THIS DEFECT AND THE FAILURE OF THE COMPONENT DOES NOT APPEAR TO HAVE DETRIMENTAL AFFECT TOT HE PERFORMANCE OF THE UNIT, IT IS CONSIDERED THAT THE DAMAGE TO THE CCA IS CONSIDERED A ONE-OFF INCIDENT AND THE WHOLE CCA WAS CHANGED.  THE CCA PN AFFECTED 1302160-102 AND 1302160-103.  NO DETAILED CIRCUIT DIAGRAMS OF THE CCA ARE AVAILABLE AS IT IS DEEMED TO BE A NON REPAIRABLE ITEM BY THE OEM.  AS A                                          
20070131000812007013100081GL  2007       1          31         2007FA0000068    120060521G3230194652          SPRING                                  BLANCA17    1731A       1220435GL  LYC   O540  IO540K1E5   41532EA                              NLG             WEAK            D      O   OTHER                                                                                           O  OTHER                                                                         LDLANDING        1                      SW15147461944                   7532156     L1214948                    AFTER AN INFLIGHT LANDING GEAR POWER PACK FAILURE, THE PILOT WAS UNABLE TO PERFORM AN EMERGENCY NOSE GEAR EXTENSION EVEN THOUGH THE MAIN GEAR WAS SAFELY EXTENDED.  DURING LANDING ROLLOUT, THE NOSE GEAR FOLDED CAUSING DAMAGE TO THE PROPELLER AND ENGINE.  AN UNSAFE NOSE GEAR INDICATION WAS SHOWN IN THE COCKPIT PRIOR TO LANDING.  PILOT STATES HE DID NOT DO (SHARP PULLUPS) AS CALLED OUT IN THE FLIGHT MANUAL IN AN ATTEMPT TO DOWNLOCK THE GEAR.  A NEW POWER PACK WAS INSTALLED, THE AIRCRAFT WAS PLACED ON JACKS AND NUMEROUS NORMAL AND EMERGENCY EXTENSIONS WERE PERFORMED, ALL WITHOUT INCIDENT, A COMPLETE CHECK WAS MADE OF THE GEAR RIGGING AND WAS FOUND CORRECT IAW MM.  THE NOSE GEAR EXTENSION SPRING WAS REMOVED AND THE 1L71 3O3  O  A18CE   1E4                  
20070129003582007012900358EU  2007       1          29         2007FA0000069    120061226G2400ZN7168752608    RELAY                                   SOCATATB20  TB20TRINIDAD8680695EU  LYC   O540  IO540*      41532EA                              ELECTRICAL SYS  FAILED          D  VJBSO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA091913S8                      1913                                    IT SEEMS THAT THE DEMAND OF THIS RELAY IN THE LANDING GEAR SYSTEM IS GREATER THAN THE DESIGNED LOAD USEAGE OF THE CURRENT RELAY.  WOULD RECOMEND A HEAVIER DUTY RELAY, WHICH MFG HAS SINCE MADE AVAILABLE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L71 3O3  ORTA51EU   1E4                  
20070220000142007022000014SO  2007       2          20         2007FA0000093    220061225G8520                CRANKSHAFT                              BLANCA17    1730A       1220433GL  CONT  O520  IO520K      17032SO                              ENGINE          BROKEN          D      O   OTHER                                                                                           O  OTHER                                                                         APAPPROACH       1                      SW1314690                       7430637     224035R                     CRANKSHAFT IS BROKEN IN AREA OF NR6, NR5 ROD JOURNAL.  CRANKSHAFT BROKE ON APPROACH TO LANDING AS PROP RPM CONTROL WAS ADVANCED ON SHORT FINAL.  ENGINE POWER UNDER VERY LOW POWER.  ENGINE HAS NOT BEEN DISASSEMBLED YET.  THERE IS ALREADY AN AD NOTE TO TAKE THESE SHAFTS OUT OF SERVICE.  IT WAS A NON VAR SHAFT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                      1L71 3O3  O  A18CE   E5CE                 
20070214000572007021400057    2007       2          14         2007FA0000094    420060929G3417702490031304    ADC                                     LEAR  35    35A         5170602CE  GARRTTTFE731TFE731*     01518WP                              FWD AVIONICS BAYFAILED          B  BSYRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL07813AS                       167                                     WHILE ENROUTE, THE PILOTS ALTIMETER FLAGGED AND OVERSPEED HORN TRIGGERED.  THE ADC BEGAN TO WORK AGAIN AT THE END OF THE FLIGHT.  THE ADC WAS FOUND TO BE DEFECTIVE AND REPLACED.  THE SYSTEM WAS TESTED AND INSPECTED AND FOUND TO COMPLY WITH FAR 91-411, PART 43 AND TO REMAIN RVSM COMPLIANT.  THERE HAS BEEN 2 PRIOR REPORTED FAILURES OF ADC`S IN THIS AIRCRAFT DATED MAY 6, 2005 AND NOV 21, 2005. (K)                                                                                                                                                                                                                                                                                                                                   2L72 4F4  F  A10CE   E6WE                 
20070131000642007013100064CE  2007       1          31         2007FA0000097    120061201G5520243400018       ELEVATOR                                LEAR  35    36LEAR      5170601CE  GARRTTTFE731TFE731*     01518WP                              RIGHT           SEPARATED       C      O   OTHER                                                                                           D  INFLIGHT SEPARATION                                                           NRNOT REPORTED   1                      EA2126FN 12042                  011                                     RT ELEVATOR DEPARTED THE AIRCRAFT AS THE AIRCRAFT EXPERIENCED AND APPROXIMATELY 70 DEGREE BANK, 50-60 DEGREE NOSE DOWN TURN.  THE PILOT WAS FLYING IN A FORMATION AND WAS BLINDED BY THE SUN AND TURNED AWAY FROM OTHER AIRCRAFT.  AS THE ELEVATOR CAME OFF OF THE HORIZONTAL STABILIZER IT TOOK BOTH HINGE BRACKETS AND THE BELLCRANK ASSY WHERE THE PUSHROD TUBE ATTACHES.  BOTH THE HORIZONTAL SKIN AT THE OB END AND THE VERTICAL CAP WHERE BELLCRANK ASSY IS LOCATED ARE TORN AND DAMAGED.  FURTHER INVESTIGATION IS IN PROGRESS INCLUDING AN ALIGNMENT AND SYMMETRY INSPECTION OF THE AIRCRAFT. STRESS WILL BE EVALUATING THESE NR TO DETERMINE THE CAUSE AND THE VIABILITY OF THE AIRFRAME FOR REPAIR.  ATTACHED IS THE IRREGULARITY REPO2L72 4F4  F  A10CE   E6WE                 
20070131001052007013100105SO  2007       1          31         2007FA0000098    120061130G27106755000         SUPPORT BRACKET                         PIPER PA28  PA28R200    7102811SO  LYC   O360  IO360A1A    41514EA                              RT AILERON      CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL034509X9000                   28R7635067                              CRACKS IN AILERON BELLCRANK LOWER SUPPORTS BOTH LT AND RT.  LOOK REAL CLOSE ON INSPECTION BECAUSE NUT AND WASHER COVER AREAS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L71 3O3  O  2A13    1E10                 
20070213001772007021300177    2007       2          13         2007FA0000099    120061109G610016160DTM        PROPELLER                                                                                                   MCAULY1C160 1C160DTM    GL                  CRACKED         B  F3PRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW15          4818                                      726964          CRACK DETECTED LENGTHWISE AT 9 INCH STATION.  LATEST LOGBOOK ENTRY FOR TSOH, DATED 7-28-2005.  (SW15200706340)  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          5  NP910     
20070213001602007021300160CE  2007       2          13         2007FA0000100    120061204G3210ART73           ROD END                                 MTSBSIMU2   MU2B36A     5780413CE  GARRTTTPE331TPE331*     01514WP                              MLG             BROKEN          B  IZ2RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW15777LP10166                  719SA                                   DURING GEAR EXTENSION FOR LANDING, A LOUD BANG WAS NOTICED BY THE PIVOT AND UNSAFE LIGHT STAYED ON.  AIRCRAFT WAS ROUTED TO MAINTENANCE AFTER LANDING.  MAINTENANCE FOUND ROD END ART -7E ON SHAFT HAD COME APART ANDALLOWED DOORS TO BECOME DISCONNECTED FROM ACTUATOR.  (SW15200706339)  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H72 3T3  T  A10SW   E2WE                 
20070213000592007021300059NE  2007       2          13         2007FA0000110    120061125G541026007           STUD                                    SKRSKYS76   S76C        8143008NE  TMECA ARRIELARRIEL1     60030NE                              RT NACELLE DOOR BROKEN          D      K   NONE                                                                                            DC INFLIGHT SEPARATION       F.O.D.                                              ININSP/MAINT     1                      EA2588CP 310                    760500      20542                       ON POST-FLIGHT INSPECTION, MAINTENANCE CREW FOUND NR 2 ENGINE COMPRESSOR FOD.  WE DISCOVERED A MISSING COWL FASTENER STUD IPC ITEM 16 FIG 53-20-03 PAGE 0.  WHEN FASTENER FAILS, THE LOCKING TAIL OF STUD FALLS INSIDE THE ENGINE AIR PLENUM AND THEN INGESTED BY ENGINE.  THIS TYPE OF FASTENER SYSTEM IS USED THROUGH OUT S76 ENGINE AIR PLENUM AREA.  THIS IS OUR 4TH EVENT OF THIS TYPE OF FAILURE CAUSING ENGINE FOD.  SUGGEST A BETTER QUALITY FASTENER THAT REMAINS INTACT UPON FAILURE, TO HELP PREVENT ENGINE FOD.  (K)                                                                                                                                                                                                                1G72 3U3  UNCH1NE    E19EU                
20070213000582007021300058NE  2007       2          13         2007FA0000111    120061215G2497SPC38G          CAP                                     SKRSKYS76   S76C        8143008NE  TMECA ARRIELARRIEL1     60030NE                              INVERTER FILTER BURNED          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA2588CP 3240                   760500                                  INVERTER WIRING:  THE CREW REPORTED THE NR 1 INVERTER CAUTION LIGHT WOULD NOT COME ON WHEN THE INVERTER WAS SELECTED OFF.  AFTER VERIFYING THE PROPER VOLTAGE AT THE RDAU THE AIRCRAFT WAS RAN AGAIN AND THE INVERTER CAUTION LIGHT WAS FUNCTIONING NORMAL.  UPON AIRCRAFT RETURN FROM A TRIP THE CREW REPORTED THE NR 2 INVERTER WAS FAILED BUT STILL SHOWED VOLTAGE INDICATION ON THE DISPLAY.  AFTER TROUBLESHOOTING THE PROBLEM A SEVERELY BURNED AND MELTED WIRE WAS FOUND IN THE AC JUNCTION BOX.  UPON REMOVAL OF THE AC JUNCTION BOX THE FOLLOWING WIRES WERE REPLACED.  (THIS WAS THE SEVERELY BURNED WIRE).  THE OTHER 2 WIRES LISTED WERE REPLACED DUE TO COLLATERAL DAMAGE FROM WIRE NR W1-036-0-22N THE INSULATION ON THESE 2 WIRES1G72 3U3  UNCH1NE    E19EU                
20070213000902007021300090WP  2007       2          13         2007FA0000116    220060828G725031081251        TURBINE BLADES                                                             GARRTTTPE331TPE33111U   01514WP                              ENGINE          SEPARATED       B      O   OTHER                                                                                           AJ FLAME/FIRE                WARNING INDICATION                                  NRNOT REPORTED   1                      WP07     349                                P44616C                     ENGINE WAS REPORTED TO HAVE FLAMES OUT OF TAILPIPE.  TEARDOWN OF ENGINE SHOWS THAT A TURBINE BLADE HAD SEPARATED AT THE FIRTREE.  BLADE DEBRIS CAUSED DAMAGE TO TURBINE OIL LINE, RESULTING IN A LEAK.  TURBINE DISC WAS REBLADED AT LAST MAINTENANCE EVENT.  TURBINE DISC/BLADES WERE PROVIDED TO MFG PROJECT ENGINEERING FOR MATERIAL ANALYSIS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                 4  T          E4WE                 
20070213001372007021300137NM  2007       2          13         2007FA0000123    120060918G53206517684         INTERCOSTAL                             BOEING737   737300      1384610NM  GE    CFM56 CFM56*      13802NE                              BS 303 S10L     CRACKED         B  I6XRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL11586US53459                  23931                                   CABIN STA 303.9 JUST ABOVE STRINGER 10L.  INTERCOSTAL OUTER CHORD ANGLE, CRACKED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA16WE   E2GL                 
20070213001422007021300142NM  2007       2          13         2007FA0000124    120060926G5330654577266       SKIN                                    BOEING737   737301      1384611NM  GE    CFM56 CFM56*      13802NE                              BS 860-885      GOUGED          B  I6XRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL11586US53459                  23931                                   UPPER FUSELAGE, STA 860 THRU 885, LBL 8 THRU RBL 8, UNDER DORSAL FIN BLADE SEAL, SKIN IS GOUGED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F4  FRTA16WE   E2GL                 
20070213001362007021300136NM  2007       2          13         2007FA0000125    120060926G5311654653146       FRAME                                   BOEING737   737301      1384611NM  GE    CFM56 CFM56*      13802NE                              BS500A S8-9R    CRACKED         B  I6XRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL11586US53459                  23931                                   UPPER FUSELAGE, BS 500A, BETWEEN STR 8R AND STR 9R, FRAME IS CRACKED AT PSU MOUNT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRTA16WE   E2GL                 
20070213001352007021300135NM  2007       2          13         2007FA0000126    120060927G531165465251        FRAME                                   BOEING737   737301      1384611NM  GE    CFM56 CFM56*      13802NE                              BS 727 S14L     CRACKED         B  I6XRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL11586US53459                  23931                                   FRAME IS CRACKED AT BODY STAION 727, STRINGER 14L.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRTA16WE   E2GL                 
20070213001402007021300140NM  2007       2          13         2007FA0000127    120060918G53116546533         FRAME                                   BOEING737   737301      1384611NM  GE    CFM56 CFM56*      13802NE                              BS 500A S8-9L   CRACKED         B  I6XRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL11586US53459                  23931                                   MID CABIN, STA 500A FRAME, BETWEEN STRINGER 8 AND 9L, CRACKED AT PSU MOUNT RAIL ATTACH POINT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F4  FRTA16WE   E2GL                 
20070215002012007021500201NM  2007       2          15         2007FA0000128    120060927G53306552988         SKIN                                    BOEING737   737301      1384611NM  GE    CFM56 CFM56*      13802NE                              BS 727 S14L     DENTED          B  I6XRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL11586US53459                  23931                                   BODY STATION 915 ABOVE STRINGER 25L LAP JOINT FUSELAGE SKIN HAS DENT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F4  FRTA16WE   E2GL                 
20070301002162007030100216NM  2007       3          1          2007FA0000129    120060924G5315BAC1518399      FLOORBEAM                               BOEING737   737301      1384611NM  GE    CFM56 CFM56*      13802NE                              FUSELAGE        GOUGED          B  I6XRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL11586US53459                  23931                                   CABIN FLOORBEAM, STA 827, WL 203.6, RBL 10, LOWER T-CAP, AFT FLANGE, GOUGED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F4  FRTA16WE   E2GL                 
20070213001412007021300141NM  2007       2          13         2007FA0000130    120060918G531169353521        FRAME                                   BOEING737   737300      1384610NM  GE    CFM56 CFM56*      13802NE                              BS 400 S8R      CRACKED         B  I6XRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL11586US53459                  23931                                   MID CABIN, STATION 400 FRAME AT STRINGER 8R, CRACKED AT PSU RAIL OUNT ATTACH POINT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F4  FRTA16WE   E2GL                 
20070213001392007021300139NM  2007       2          13         2007FA0000131    120060918G531065807351        CREASE BEAM                             BOEING737   737300      1384610NM  GE    CFM56 CFM56*      13802NE                              BS 947-992 S17R CORRODED        B  I6XRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL11586US53459                  23931                                   AFT GALLEY DOOR CREASE BEAM INNER CHORD ANGLE, BS 947 TO 992, STRINGER 17R, WL 208, CORROSION OUT OF LIMITS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F4  FRTA16WE   E2GL                 
20070213001612007021300161NM  2007       2          13         2007FA0000132    120060817G5315BAC1518399      FLOORBEAM                               BOEING737   737301      1384611NM  GE    CFM56 CFM56*      13802NE                              BS 312          CORRODED        B  I6XRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL11586US53459                  23931                                   CABIN BS 312, FROM LBL 55 TO RBL 55 WL 208, FLOORBEAM HAS LIGHT CORROSION.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA16WE   E2GL                 
20070220001792007022000179NM  2007       2          20         2007FA0000133    120060924G531165465935        FRAME                                   BOEING737   737301      1384611NM  GE    CFM56 CFM56*      13802NE                              FUSELAGE        CRACKED         B  I6XRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL11586US53459                  23931                                   CABIN, BS 787, FRAME AT STR 8R, CRACKED AT STOW BIN ATTACH BRACKET.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F4  FRTA16WE   E2GL                 
20070220001802007022000180NM  2007       2          20         2007FA0000134    120060924G53126545409245      PRESSURE PANEL                          BOEING737   737301      1384611NM  GE    CFM56 CFM56*      13802NE                              FUSELAGE        CRACKED         B  I6XRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL11586US53459                  23931                                   MID CABIN BS 663, LBL 31, WHEEL WELL PRESSURE DECK WEB, CRACKED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F4  FRTA16WE   E2GL                 
20070227000802007022700080NM  2007       2          27         2007FA0000135    120060927G531165465251        FRAME                                   BOEING737   737301      1384611NM  GE    CFM56 CFM56*      13802NE                              BS 727 S4L      CRACKED         B  I6XRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL11586US53459                  23931                                   FRAME IS CRACKED AT BODY STATION 727, STRINGER 14L.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F4  FRTA16WE   E2GL                 
20070301002062007030100206NM  2007       3          1          2007FA0000136    120060924G53206580736689      FITTING                                 BOEING737   737301      1384611NM  GE    CFM56 CFM56*      13802NE                              FUSELAGE        CORRODED        B  I6XRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL11586US53459                  23931                                   DOOR 1R, BS 306-312, WL 248-249, LBL 57-63, SERPENTINE PLATE CASTING CORRODED AROUND FASTENER HOLES.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F4  FRTA16WE   E2GL                 
20070301002092007030100209NM  2007       3          1          2007FA0000137    120060918G5340693535214       STRINGER CLIP                           BOEING737   737300      1384610NM  GE    CFM56 CFM56*      13802NE                              FUSELAGE        CRACKED         B  I6XRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL11586US                       23931                                   PASSENGER CABIN, STATION 639 AT STRINGER 4L, STRINGER CLIP, CRACKED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F4  FRTA16WE   E2GL                 
20070301002132007030100213NM  2007       3          1          2007FA0000138    120060918G5311                FRAME                                   BOEING737   737300      1384610NM  GE    CFM56 CFM56*      13802NE                              FUSELAGE        CRACKED         B  I6XRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL11586US53459                  23931                                   MID CABIN, STATION 480 FRAME, AT STRINGER 8L, CRACKED AT PSU MOUNT RAIL ATTACH POINT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F4  FRTA16WE   E2GL                 
20070301002182007030100218NM  2007       3          1          2007FA0000139    120060918G53116546533         FRAME                                   BOEING737   737300      1384610NM  GE    CFM56 CFM56*      13802NE                              FUSELAGE        CRACKED         B  I6XRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL11586US                       23931                                   MID CABIN, STATION 500A FRAME, BETWEEN STRINGER 8 AND 9L, CRACKED AT PSU MOUNT RAIL ATTACH POINT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA16WE   E2GL                 
20070301002172007030100217NM  2007       3          1          2007FA0000140    120060918G521069773671        SUPPORT                                 BOEING737   737300      1384610NM  GE    CFM56 CFM56*      13802NE                              R2 DOOR         CRACKED         B  I6XRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL11586US                       23931                                   AT FWD CABIN STA 328+6, DOOR 2R AFT STOP FTG INTERCOSTAL TEE SUPPORT, CRACKED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F4  FRTA16WE   E2GL                 
20070301002032007030100203CE  2007       3          1          2007FA0000142    120061126G5210MJV3            VALVE                                   CESSNA500   550         2076604CE                                                               CABIN DOOR      OUT OF POSITION E  ON0AB   EMER. DESCENT                                                                                   O  OTHER                                                                         NRNOT REPORTED   1                      GL0550NF                        5500636                                 AT G; 390 15A, -12 DEGREES CABIN DOOR SEAL DEFLATED NECESSATING AN EMERGENCY DESCENT TO 10,000 FT.  AFTER 5-8 MINUTES, DOOR SEAL RE-INFLATED OPERATION WAS NORMAL, CONDITION DID NOT REOCCUR.  FOUND DOOR SEAL VALVE WARM AIR TUBE BLAOCKED BY TAPE AND OUT OF POSITION.  REMOVED TAPE, POSITIONED WARM AIR TUBE PROPERLY.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                 1L72 4F      A22CE                        
20070226001542007022600154CE  2007       2          26         2007FA0000143    120061126G27200510105207      CONTROL CABLE                           CESSNA172   172M        2072418CE  LYC   O320  O320*       41508EA                              RUDDER          BROKEN          D      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             APAPPROACH       1                      SO191653V4993                   17263703                                RUDDER CONTROL CABLE BRAKES DURING FLIGHT TRAINING WHILE PERFORMING FORWARD SLIP MANEUVER ON FINAL APPROACH.  INITIAL INSPECTION SHOWS CABLE BROKE JUST FORWARD OF TERMINAL END AT THE LOWER BELL CRANK.  FURTHER INSPECTION REVEALED THE CAUSE OF FAILURE TO BE CORROSION INSIDE THE STEEL CABLE (PN 0510105207).  SINCE THE LOWER RUDDER BELLCRANK AREA IS EXPOSED TO THE ELEMENTS OUTSIDE OF THE AIRCRAFT, RECOMMENDATIONS IS TO REPLACE THE RUDDER CONTROL CABLE WITH STAINLESS STEEL TYPE (PN 0510105305) AVAILABLE FROM THE OEM.  (K)                                                                                                                                                                                                     1H71 3O3  ONT3A12    E274                 
20070309003342007030900334SO  2007       3          9          2007FA0000152    220061020G8530SA52006A1       CYLINDER                                CESSNA207   207A        2073604CE  CONT  O520  IO520F      17032SO                                              CRACKED         B  CY4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03     900                                                            PRESSURE TESTED AT 90 PSI WITH SOAPY WATER APPLIED TO EXHAUST SIDEWALL.  AIR LEAKAGE NOTED BETWEEN FINS 19/20 & 20/21.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1H71 3O3  O  A16CE   E5CE                 
20070309003352007030900335SO  2007       3          9          2007FA0000153    220061020G8530SA52006A1       CYLINDER                                CESSNA207   207A        2073604CE  CONT  O520  IO520F      17032SO                                              CRACKED         B  CY4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03     900                                                            PRESSURE TESTED AT 90 PSI WITH SOAPY WATER APPLIED TO EXHAUST SIDE WALL.  AIR LEAKAGE NOTED BETWEEN FINS 19/20 AND 20/21.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H71 3O3  O  A16CE   E5CE                 
20070309003362007030900336SO  2007       3          9          2007FA0000154    220061020G8530SA52006A1       CYLINDER                                CESSNA207   207A        2073604CE  CONT  O520  IO520F      17032SO                                              CRACKED         B  CY4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03                                                                    PRESSURE TESTED AT 90 PSI WITH SOAP WATER APPLIED TO EXHAUST SIDEWALL.  AIR LEAKAGE NOTED BETWEEN FINS 19/20 AND 20/21.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H71 3O3  O  A16CE   E5CE                 
20070301002412007030100241CE  2007       3          1          2007FA0000160    120061216G551445A21085003     BRACKET         BEECH                   BEECH MU300 400A        1155402CE  PWA   JT15  JT15D5      52112NE                              HORIZ STAB      CRACKED         B  E81RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL0393XP 7251                   RK74                                    DURING INSPECTION OF HORIZONTAL STABILIZER ROLLER BRACKETS AND STRUCTURE IAW COMMUNIQU NR 70, FOUND LT HORIZONTAL STABILIZER FWD ROLLER BRACKET, PN 45A21085-003, AND LT AFT ROLLER BRACKET, PN 45A21086-003, BOTH CRACKED.  MFG AC TECH SUPPORT BELIEVES IMPROPER VERTICAL STABILIZER TO ROLLER GAP CLEARANCES MAY BE CONTRIBUTING TO PROBLEM.  INSPECTION AREA NOT CURRENTLY NOTED ON MM AND 5-20-02 INSPECTION GUIDES, REQUIRES BORESCOPE TO INSPECT UNDERLYING STRUCTURE.  RECOMMEND A 1-TIME SB AND/OR SAIB.  SHOULD BE ADDED TO INSPECTION GUIDES.  (K)                                                                                                                                                                                  2H72 4F4  FRTA16SW   E25EA                
20070301002512007030100251CE  2007       3          1          2007FA0000161    120061213G3310                TRANSISTOR                              CESSNA525   525         2076601CE  WILINTFJ44  FJ44        66000GL                              COCKPIT         SHORTED         B  E81RO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL0366AM 2398                   5250160                                 INVESTIGATED COCKPIT OVERHEAD FLOODLIGHTS TRIPPING ASSOCIATED CB WHEN BATTERY POWER APPLIED TO AIRCRAFT.  FOUND ATTACHING SCREW FOR QC001 TRANSISTOR SHORTING TO AIRFRAME.  ALSO, FOUND RESISTOR NR150 ON THRUST ATTENTUATOR PC BOARD NZ017 BURNED.  REPAIRS REQUIRED REPLACING QC001 TRANSISTOR AND BASE, INSULATING QC001 ATTACHING SCREW, REPLACING DIODE DC046, AND REPLACING PC BOARD JC045.  RECOMMENDED FURTHER INVESTIGATION TO DETERMINE IF A FLEET PROBLEM REQUIRING MODIFICATIONS TO PREVENT TRANSISTOR ATTACHING SCREW FROM SHORTING TO AIRFRAME.  (K)                                                                                                                                                                              1L72 4F4  FRTA1WI    E3GL                 
20070309001692007030900169    2007       3          9          2007FA0000197    420060904G2565BACR12BU9B      RING            AIRCRUISERS             BOEING727   72722C      138400FNM                                                               EVAC SLIDE      ELONGATED       D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO01942UP           1128        19101                                   DURING ROUTINE C-CHECK INSPECTION OF FORWARD DOOR EMERGENCY ESCAPE SLIDE, THE SLIDE BUSTLE LATCH CHAIN WAS FOUND DETACHED FROM THE SPLIT RING.  THE SPLIT RING HAD BECOME ELONGATED AND THE RING COILS HAD SEPARATED THUS ALLOWING THE CHAIN TO DETACH.  THE SLIDE WOULD NOT HAVE INFLATED IF REQUIRED.  THE SPLIT RING HAS BEEN REPLACED.  (K)                                                                                                                                                                                                                                                                                                                                                                                                 2L73 4F      A3WE                         
20070402002202007040200220CE  2007       4          2          2007FA0000198    120060726G5210511150480       BOLT                                    CESSNA421   421C        2076016CE  CONT  O520  GTSIO520*   17032SO                              PAX DOOR        CORRODED        B  AW4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP11485DS4783                   421C0459                                DURING ACCOMPLISHMENT OF ANNUAL INSPECTION, EXCESSIVE PLAY WAS NOTED AT AFT HINGE POINT OF UPPER MAIN CABIN DOOR.  INVESTIGATION REVEALED THAT HINGE BOLT WAS BROKEN, HEAD OF BOLT COULD BE TURNED, BUT END WITH NUT WOULD NOT FOLLOW.  TRIED TO REMOVE BOLT BUT WAS UNABLE TO REMOVE EITHER PIECE.  ATTEMPTED TO REMOVE FORWARD BOLT AS THE WHOLE DOOR ASSY HAD TO BE REMOVED FOR FURTHER INSPECTION, BUT WERE UNABLE TO REMOVE IT EITHER.  HAD TO FINALLY REMOVE HINGES FROM DOOR AND REMOVE HINGE SUPPORTS FROM THE FUSELAGE STRUCTURE.  FOUND THAT THE BOLTS AND BUSHINGS IN THE HINGES WERE EXCESSIVELY CORRODED WHICH PREVENTED THEM FROM BEING REMOVED.  IN ORDER TO DISASSEMBLE THE FWD HINGE, IT WAS NECESSARY TO HACKSAW OFF THE HEAD 1L72 3O3  O  A7CE    E7CE                 
20070309000442007030900044EA  2007       3          9          2007FA0000213    220060627G8520LW18372         CRANKCASE       LYC         O320D3G     PIPER PA28  PA28161     7102803SO  LYC   O320  O320D3G     41508EA                              ENGINE          CRACKED         D      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      EA178391Y4648 280   RL1519539A  288116235   RL1519539A                  DURING 100 HOUR INSPECTION A CRACK WAS DISCOVERED ON RT CRANKCASE HALF.  THE CRACK (APPROXIMATELY 1 INCH) ORIGINATED FROM A LOWER PARTING FACE BOLT HOLE AND SHOWED EVIDENCE OF OIL LEAKAGE ONTO MUFFLER SHROUD (BURNED OIL).  SPECIFIC CAUSE OF CRACK UNKNOWN.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L71 3O3  O  2A13    E274                 
20070309003372007030900337SO  2007       3          9          2007FA0000216    220060821G8530SA52006A1       CYLINDER                                CESSNA207   207A        2073604CE  CONT  O520  IO520F      17032SO                                              CRACKED         B  CY4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03     690                                                            PENETRANT TEST INDICATES CRACKS BETWEEN FINS 20/21 ADJACENT TO THE EXHAUST SEAT AND BETWEEN 19/20 NEARER TO THE UPPER SPARK SPLUG SIDE OF THE EXHAUST CHAMBER.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3O3  O  A16CE   E5CE                 
20070322000742007032200074SW  2007       3          22         2007FA0000239    120061020G33001220            LIGHT                                   AIRTRCAT802 AT802       0390305SW                                                                               FAILED          F      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      AGAGRICULTURE    1                      NM09                                                                    PULSELIGHT UNIT FAILED.  EVALUATION OF FAILED UNIT REVEALED HIGH HEAT GENERATED WITHIN UNIT AND SIGNIFICANT BURNING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L71 3T    NCA19SW                        
20070326000992007032600099NM  2007       3          26         2007FA0000248    120061216G2497                WIRE HARNESS                            DOUG  MD80  MD83        3023681NM                                                               BS 905          CHAFED          G      A   UNSCHED LANDING                                                                                 A  FLAME/FIRE                                                                    CLCLIMB          1                      GL03                                                                    MAIN CABIN AT RT STATION 905 WIRING BUNDLE CHAFED THROUGH ON PARTITION CAUSING FIRE AND SMOKE DAMAGE.  THE PARTITION AND THE WIRING BUNDLE LOCATIONS WERE INSTALLED AND POSITION AS PART OF AN EXECUTIVE CABIN INTERIOR MODIFICATION.  50 + WIRES, INTERIOR PANELS, INSULATION BLANKETS AND ONE CEILING RAIL WERE DAMAGED.                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F    RT                             
20070507000082007050700008CE  2007       5          7          2007FA0000347    120061203G32203A07000001      SCREW                                   CESSNA206   U206F       2073333CE  CONT  O520  IO520*      17032SO                              NLG             DEPARTED        D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA078JZ                         U20602326                               AIRCRAFT HAD GEAR UP LANDING, FOUND SCREW PN AN503-8-4 HAD FALLEN OUT.  SCREW WAS TO BE SAFTIED, NO SAFETY WIRE FOUND.  ONCE SCREW FELL OUT THE POWER PISTON HOUSING PN 3A07402-002 WAS ALLOWED TO FLEX DURING SUB CYCLES ALLOWING THE SCREW TO TEAR THE ORING ON THE HOUSING FLANGE AND PUMP ALL THE HYD (5606) FLUID OVERBOARD AND NOT ALLOWING THE MAIN GEAR THE EXTEND.  THE SCREW HOLE WHERE THE SCREW FELL OUT ON THE PISTON HOUSING TORE OUT.  REPLACED THE PISTON HOUSING PN 3A07000-001, ALL ORINGS AND INSTALLED NEW SCREWS PN AN503-8-4 AND SAFTIED.  SWING LDG 6X`S AND RELEASED AIRCRAFT.  (K)                                                                                                                                     1H71 3O3  O  A4CE    E5CE                 
20070504001672007050400167CE  2007       5          4          2007FA0000376    120060907G781002R3022406      EXHAUST DUCT                            BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA                              RT ENGINE       CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO09     11322431                           PCE85195                    WHILE PERFORMING SCHEDULED MAINTENANCE,REMOVED LT ENGINE EXHAUST STACK TO FACILITATE INSPECTING THE EXHAUST DUCT. FOUND CRACK FOLLOWING THE CIRCUMFERENCE OF THE SKI SLOPE. THE EXHAUST DUCT HAD PWA SB 3380 COMPLIED WITH 431 HOURS EARLIER.  POWER SECTION WAS REMOVED AND SENT FOR REPAIR.                                                                                                                                                                                                                                                                                                                                                                                                                                                   1L72 4T4  T  A24CE   E4EA                 
20070613002222007061300222CE  2007       6          13         2007FA0000407    120060904G781002R3022406      EXHAUST DUCT                            BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA                              ENGINE          CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO09     13769657                                                       WHILE PREFORMING SCHEDULED MAINTENANCE,REMOVED EXHAUST STACKS TO FACILTATE INSPECTING THE EXHAUST DUCT.A CRACK WAS FOUND IN THE SKI SLOPE.POWER SECTION WAS REMOVED FOR REPAIR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L72 4T4  T  A24CE   E4EA                 
20070613002242007061300224CE  2007       6          13         2007FA0000409    120060812G781002R3022406      EXHAUST DUCT                            BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA                              ENGINE          CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO09     14327979                                                       WHILE PREFORMING SCHEDULED MAINTENANCE,REMOVED EXHAUST STACKS TO FACILTATE INSPECTING THE EXHAUST DUCT.A CRACK WAS FOUND IN THE SKI SLOPE.POWER SECTION WAS REMOVED FOR REPAIR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L72 4T4  T  A24CE   E4EA                 
20070604000022007060400002WP  2007       6          4          2007FA0000418    120060501G6210C0165           BLADE                                   ROBSINR44   R44RAVENII  7640122WP                                                               MAIN ROTOR      DEBONDED        D      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         O  OTHER                                                                         CRCRUISE         1                      SW99CFICL5    1                                                         IN FLIGHT BREAK UP. HELICOPTER CRASHED KILLED 2 HUMANS. NO REACTION TIME TO LAND SAFELY, PILOT WAS EJECTED OUT OF SEAT BY BLADE, KILLED INSTANTLY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1G71 3O      H11NM                        
20070613002192007061300219CE  2007       6          13         2007FA0000424    120060820G781002R3022406      EXHAUST DUCT                            BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA                              ENGINE          CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO09     139262030                                                      WHILE PREFORMING SCHEDULED MAINTENANCE,REMOVED EXHAUST STACKS TO FACILTATE INSPECTING THE EXHAUST DUCT.A CRACK WAS FOUND IN THE SKI SLOPE.POWER SECTION WAS REMOVED FOR REPAIR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L72 4T4  T  A24CE   E4EA                 
20070613002132007061300213CE  2007       6          13         2007FA0000432    120060705G781002R3022406      EXHAUST DUCT                            BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA                              ENGINE          CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO09     11753431                                                       WHILE PREFORMING SCHEDULED MAINTENANCE,REMOVED EXHAUST STACKS TO FACILTATE INSPECTING THE EXHAUST DUCT.A CRACK WAS FOUND IN THE SKI SLOPE.THE EXHAUST DUCT SB 3380 HAD BEEN COMPLIED WITH 515.2 HOURS PRIOR.POWER SECTION WAS REMOVED FOR REPAIR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L72 4T4  T  A24CE   E4EA                 
20070613002202007061300220CE  2007       6          13         2007FA0000441    120060908G781002R3022406      EXHAUST DUCT                            BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA                              ENGINE          CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO09     16012660                                                       WHILE PREFORMING SCHEDULED MAINTENANCE,REMOVED EXHAUST STACKS TO FACILTATE INSPECTING THE EXHAUST DUCT.A CRACK WAS FOUND IN THE SKI SLOPE.POWER SECTION WAS REMOVED FOR REPAIR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L72 4T4  T  A24CE   E4EA                 
20070613001692007061300169WP  2007       6          13         2007FA0000449    120060501G6210C0165           BLADES                                  ROBSINR44   R44RAVENII  7640122WP                                                               MAIN ROTOR      DEBONDED        C      BE  EMER. DESCENT           ENGINE SHUTDOWN                                                         O  OTHER                                                                         CRCRUISE         1                      SW99CFICL5    1                                                         IN FLIGHT BREAK UP. HELICOPTER CRASHED KILLED 2 HUMANS. NO REACTION TIME TO LAND SAFELY, PILOT WAS EJECTED OUT OF SEAT BY BLADE KILLED INSTANTLY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1G71 3O      H11NM                        
20070605002142007060500214CE  2007       6          5          2007FA0000452    120061212G3600IU478003        PISTON                                  CESSNA172   172M        2072418CE  LYC   O320  O320*       41508EA                              AIR PUMP        FAILED          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      NE019899Q65                     17265843    L42B2427A                   INSTALLED A PISTON AIR PUMP (PN IU478-003, SER NR T568A) ON AUG 25, 2005.  THE PUMP DRIVE COUPLING FAILED BY 12/06 WITH LESS THAN 66 HOURS ON IT.  COUPLING FAILED INTERNALLY IN PUMP, WITH PLASTIC/SILICON DEBRIS IN ENG/DRIVE INTERFACE. (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H71 3O3  ONT3A12    E274                 
20070808000592007080800059CE  2007       8          8          2007FA0000663    120061121G5740187504          CONTROL ARM                             BEECH 18    RC45J       1151021CE  PWA   R985  R985*       52008NE                              ELEVATOR        CRACKED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO03145J 9544                   51233                                   DURING COMPLIANCE WITH AD 77-19-07 PARA B, DYE PENETRANT INSPECTION REVEALED 2 POSSIBLE DEFECTS, 0.75 INCH AND 0.5 INCH LONG.  BOTH INDICATIONS RADIATING FROM THE TAPERED PIN ON THE STARBOARD SIDE OF THE CONTROL ARM.  INDICATIONS CONTINUED TO APPEAR AFTER REPEATED SURFACE POLISHING AND DYE PENTRANT, ALTHOUGH NO DEFINITIVE.  OTHER DEFECTS AND/OR INDICATIONS OBSERVED.  INDICATIONS MAY NOT ACTUALLY HAVE BEEN A CRACK, THE INTERMITTENT LINES MAY BE OLD SURFACE FLAWS.  HOWEVER, IT WAS DECIDED THAT THE BEST COURSE OF ACTION WAS TO REPLACE PART.  OLD PART DID HAVE THE SMALLER AN 386-3-18 TAPERED PINS, INSTEAD OF THE LARGER, AN 386-5-18 PINS USED ON THE LATER MFG ELEVATOR CONTROL ARMS, THIS MAY HAVE BEEN A CONTRIBUTING 1L72 3R3  R  A765    5E1                  
20070906000422007090600042SW  2007       9          6          2007FA0000734    120060724G2424800397501       VOLT REGULATOR                          MOONEYM20   M20R        5870225SW  CONT  O550  IO550*           SO                                              FAILED          D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL25999JW296                    290293                                  THE INABILITY OF THE VOLTAGE REGULATOR (PN 800397-501, SN 0165) TO CONTROLTHE OUTPUT OF THE ALTERNATOR WHEN THE BATTERY SWITCH WAS TOGGLED BETWEEN THE NR1 AND NR 2 BATTERY, IN FLIGHT.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L71 3O3  ORT2A3     E3SO                 
20070917000732007091700073    2007       9          17         2007FA0000756    420061112G256546FASA0303603   LIFE RAFT                               AMD   FALC20FALCON      2720302EU  GARRTTTFE731TFE73160         NE                                              PARTIAL INFLATE B  QLCRO   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      GL11191MC                       282                                     THE LIFE RAFT VACUUM BAG INFLATED DUE TO CYLINDER LEAKAGE BETWEEN THE CYLINDER HEAD AND LIFE RAFT CYLINDER.  THE AC WAS CRUISING AT 40,000 FT WHEN THE PILOT HEAR A LOUD POP.  UPON INVESTIGATION, THE PILOT HAD DISCOVERED THE LIFE RAFT HAD AN UNCOMMANDED INFLATION.  THE BANDS AROUND THE LIFE RAFT CONTAINER HELD THE LIFE RAFT TOGETHER AND IT WAS LATER REMOVED FROM UNDER THE COUCH.                                                                                                                                                                                                                                                                                                                                                    2L72 4F4  F  A7EU    E1NM                 
20070917000682007091700068    2007       9          17         2007FA0000757    420061016G256546FASA2311323   LIFE RAFT                                                                                                                                               PARTIAL INFLATE B  QLCRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL11                                                                    LIFE RAFT PARTIALLY INADVERTENTLY INFLATED IN CUSTOMERS AC CABIN AREA (UNDER SEAT CUSHION) WHICH COULD HAVE POSSIBLY CAUSED SEVERE DAMAGE TO THE AIRCRAFT, INJURY TO PERSONS OR LOSS OF AIRCRAFT CONTROL HAD LIFE RAFT COMPLETELY INFLATED IN-FLIGHT.  THE LIFE RAFT WAS REMOVED FROM THE AIRCRAFT CABIN BY THE OPERATOR BEFORE IT HAD COMPLETELY INFLATED MINIMIZING THE POSSIBILITY OF SEVERE DAMAGE.  IT WAS DETERMINED THAT THE INFLATION CYLINDER HEAD WAS LEAKING AT THE POINT WHERE  IT ATTACHES TO THE INFLATION CYLINDER.  THIS LIFE RAFT WAS NOT COVERED UNDER THE MFG SIL (SIL001STS) DATED 11/21/2005.  (K)                                                                                                                                                                   
20071204001062007120400106CE  2007       12         4          2007FA0000993    120060828G2750SM50D7          RELAY                                   BEECH 200   B200        1152922CE                                                               TE FLAP MOTOR   INTERMITTENT    D      O   OTHER                                                                                           S  AFFECT SYSTEMS                                                                DEDESCENT        1                      WP19185XP514                    BB952                                   DURING FLIGHT WHEN THE FLAPS SELECTED DOWN & DID NOT RESPOND.  AIRCRAFT LANDED IN A FLAPS UP CONDITION & DELIVERED TO MAINTENANCE. INVESTIGATION REVEALED THE FLAP MOTOR POWER RELAY WAS OPERATING INTERMITTENTLY.  A NEW FLAP MOTOR RELAY, PROCURED FROM RAPID (RAYTHEON PARTS INVENTORY AND DISTRIBUTION SYSTEM) WAS INSTALLED AND THE MALFUNCTION WAS RESOLVED.  THE REMOVED / FAILED RELAY HAD BEEN IN SERVICE 22 MONTHS AND 514.5 FLIGHT HOURS.                                                                                                                                                                                                                                                                                            1L72 4T      A24CE                        
20060711001072006071100107EA  2006       7          11         2050506          220060621G7414                BUSHING         LYC         IO360A3B6D  MOONEYM20   M20J        5870219SW  LYC   O360  IO360A3B6   41514EA                              MAGNETO DRIVE   LACK OF LUBE    B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NE01386OH           568         241044      L2178051A                   CRANKCASE WAS FIELD REPAIRED BY INSTALLING A BUSHING IN THE MAGNETO DRIVE GEAR BOSS. IT APPEARS THE OIL SUPPLY HOLE WAS NOT DRILLED IN THE BUSHING. THE BUSHING WAS STARVED FOR OIL AND METAL WAS FOUND IN THE OIL AND FILTER, THE BUSHING WAS LOOSE AND DAMAGED FROM OIL STARVATION.                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L71 3O3  O  2A3     1E10                 
20060512000632006051200063CE  2006       5          12         21200003AD       120060510G2730083200054       HINGE                                   CESSNA421   421B        2076014CE                                                               ELEVATOR        DAMAGED         B      O   OTHER                                                                                           O  OTHER                                                                         DEDESCENT        1                      SW991944G8307                   421B0844                                CUSTOMER REPORTED VIBRATION AT HIGH SPEEDS. INSPECTED AIRCRAFT AND FOUND CENTER ELEVATOR HINGE INBOARD AND OUTBOARD BRACKETS ELONGATED ON THE RIGHT ELEVATOR. INSTALLED CESSNA SERVICE KIT SK421-130B REPLACING ALUMINUM ELEVATOR HINGE BRACKETS WITH STAINLESS STEEL BRACKETS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L72 3O      A7CE                         
20060803000602006080300060GL  2006       8          3          25869            320060725G6110                STRUCTURE       MCAULY                  CESSNA172   172S        2072439CE  LYC   O360  IO360A1A    41514EA  MCAULY1A170 1A170E      GL  PILOT BORE      CRACKED         B  W59RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP07428DW2099       TI014       172S8708                TI014           PROPELLER PILOT BORE FOUND CRACKED BY PENETRANT INSPECTION BEING PERFORMED DURING OVERHAUL                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1H71 3O3  ONT3A12    1E10    5  NP857     
20060516000912006051600091CE  2006       5          16         314901           120060511G3246314901          WHEEL                                   CESSNA500   550         2076604CE                                                               MLG             CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW07                                                                    FINDING FATIGUE CRACKS FORMING AT THE INTERSECTION OF THREADED HOLE AND DRILLED PASSAGE OF FUSE PLUG HOLE AND VALVE STEM HOLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L72 4F      A22CE                        
20060321002102006032100210CE  2006       3          21         3969             120060224G282000292000051     LINE                                    BEECH 58    58          1152740CE                                                               ZONE 600        CHAFED          B  PAI5K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO056458C7236                   TH1495                                  DURING SCHEDULED INSPECTION FOUND FUEL CROSSFEED LINE IN RT WHEEL WELL CHAFED 75 PERCENT THROUGH BY LANDING GEAR RETRACT ROD.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1L72 3O      3A16                         
20060315001382006031500138SO  2006       3          15         4381             120060207G242051530007B       GCU                                     PIPER PA30  PA30        7103002SO                                                               LT GEN          INOPERATIVE     B      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      NE031509                        30798                                   AIRCRAFT CAME IN FOR GENERATOR PARALLELING.  LEFT GENERATOR CONTROL UNIT NEEDED REPLACEMENT.  INSTALLED OVERHAULED GCU S/N 10853A; GCU FAILED ON INITIAL RESET.  INSTALLED SECOND GCU S/N 9183; GCU FAILED ON INITIAL RESET. (BOTH ABOVE GCU'S HAD JUST BEEN OVERHAULED BY PRECISION ELECTRONICS, INC., ATLANTA, GA FOR THE SAME INITIAL FAILURE PROBLEM).  INSTALLED A THIRD GCU S/N 9657; WHICH FUNCTIONED CORRECTLY.  (ALSO OVERHAULED BY PRECISION ELECTRONICS, INC.)                                                                                                                                                                                                                                                                       1L72 3O      A1EA                         
20060315001742006031500174CE  2006       3          15         4381002          120060207G242051530007B       GCU                                     BEECH 200   B200        1152922CE                                                               LT GEN          MALFUNCTIONED   B      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      NE031509G                       BB1308                                  AIRCRAFT CAME IN FOR GENERATOR PARALLELING.  LEFT GENERATOR CONTROL UNIT NEEDED REPLACEMENT.  INSTALLED OVERHAULED GCU S/N 10853A; GCU FAILED ON INITIAL RESET.  INSTALLED SECOND GCU S/N 9183; GCU FAILED ON INITIAL RESET.  BOTH ABOVE GCU'S HAD JUST BEEN OVERHAULED BY PRECISION ELECTRONICS, INC., ATLANTA, GA FOR THE SAME INITIAL FAILURE PROBLEM.  INSTALLED A THIRD GCU S/N 9657; WHICH FUNCTIONED CORRECTLY, ALSO OVERHAULED BY PRECISION ELECTRONICS, INC.                                                                                                                                                                                                                                                                           1L72 4T      A24CE                        
20060512001282006051200128SO  2006       5          12         4437811          120060418G7160P151936         AIR FILTER                              PIPER PA32  PA32R301T   7103220SO                                                               ENGINE          DEBONDED        B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL0930538                       3257343                                 PN P560007-3, GASKET HAD SEPERATED FROM FILTER ON ONE SIDE AND WAS PULLED INTO THE AIR STREAM ON THE ENGINE SIDE OF THE FILTER.  INSTALLED NEW FILTER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L71 3O      A3SO                         
20061025001062006102500106EA  2006       10         25         5292S1006        220061013G8530                EXHAUST VALVE                           PIPER PA28  PA28140     7102802SO  LYC   O320  O320*       41508EA                              ENGINE          SEPARATED       D      A   UNSCHED LANDING                                                                                 YJ ENGINE STOPPAGE           WARNING INDICATION                                  CRCRUISE         1                      CE075292S                       2826923                                 PILOT REPORTED ENGINE VIBRATION FOLLOWED BY PROGRESSING LOSS OF POWER WHICH EVENTUALLY LED TO COMPLETE LOSS OF POWER AND ENGINE FAILURE.  PILOT EXECUTED AN UNEVENTFUL EMERGENCY LANDING ON A PAVED STATE HIGHWAY.  NO DAMAGE TO AIRCRAFT UPON LANDING. UPON EXAMINATION OF THE ENGINE, FOUND NR 3 CYLINDER EXHAUST VALVE HEAD FAILURE AND FRAGMENTS OF FAILED EXHAUST VALVE HEAD FOUND IN INDUCTION SYSTEM.                                                                                                                                                                                                                                                                                                                                    1L71 3O3  O  2A13    E274                 
20060413002602006041300260SO  2006       4          13         5784607          120060215G272063457003        ARM                                     PIPER PA32  PA32300     7103212SO                                                               RUDDER CONTR    BROKEN          C      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      GL194209R5100                   3240574                                 ONE OF THE THE CLIPS (PIPER PN 62832-000) IN THE RUDDER TRIP TUBE YIELDED AND SLIPPED OVER THE END OF THE SPRING. THIS CAUSED THE RUDDER TRIM SPRING TO BIND IN ITS TUBE, RESULTING IN THE RUDDER CONTROL ARM (PIPER PN 63457-003) BREAKING WHERE THE TRIM ATTACHES. THIS CAUSED LOSS OF RUDDER TRIM AND NOSE-WHEEL CENTERING. RUDDER CONTROL AND NOSEWHEEL STEERING WERE UNAFFECTED.I HAVE PHOTOS OF THE FAILED PARTS I CAN EMAIL IF SOMEONE LET'S ME KNOW WHERE TO SEND THEM.                                                                                                                                                                                                                                                                 1L71 3O      A3SO                         
20060724000302006072400030GL  2006       7          24         60806            320060608G6111FC7663R         BLADE           HARTZL                                                     LYC   O540  IO540K1K5   41532NE  HARTZLHCC3Y HCC3YR      GL  PROPELLER       CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO17     854  854   EL223A      1800                    EL223A          CRACKED BLADE SHANK.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   3  O          1E4     5  CP25EA    
20060724000222006072400022GL  2006       7          24         608062           320060608G6111D68315A         CLAMP           HARTZL                  GULSTM500   500         0141K02SW  LYC   O540  O540*       41532EA  HARTZLHCA2  HCA2MVK2    GL  PROPELLER       CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO17     1008       HWA49       791                     HWA49           BLADE CLAMPS CRACKED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1H72 3O3  ORT6A1     E295    5  CP24EA    
20060724000242006072400024GL  2006       7          24         608063           320060608G6111D68315A         CLAMP           HARTZL                  GULSTM500   500         0141K02SW  LYC   O540  O540*       41532EA  HARTZLHCA2  HCA2MVK2    GL  PROPELLER       CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO17     1008       HWA49       791                     HWA49           BLADE CLAMP CRACKED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H72 3O3  ORT6A1     E295    5  CP24EA    
20060518001802006051800180SW  2006       5          18         77669            120060301G6100                HUB             HARTZL      HCB3Z302    GULSTM680   680F        0141606SW                                   HARTZLHCB3Z HCB3Z302    GL  PROPELLER       CORRODED        B  EY2RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03                                                                    CORRODED CLAMP ASSEMBLY, PN 838-17, SN J4324, U4701, U4646.  CORRODED BLADES MODEL NR 9349, SN A41967, A41996, A41251.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H72 3O      2A4             5  CP907     
20060512000482006051200048GL  2006       5          12         77670            320060213G6110                CLAMP                                   GULSTM680   680F        0141606SW                                   HARTZLHCB3Z HCB3Z302    GL  PROPELLER ASSY  CORRODED        B  EY2RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03                                                                    CORRODED CLAMP ASSEMBLY PN 838-17, SN U5211, U5188, U5109.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1H72 3O      2A4             5  CP907     
20060518001792006051800179GL  2006       5          18         78978            320060306G6114D7292C203       HUB                                     CESSNA182   182         2072702CE                                   MCAULY2A34C 2A34C203    GL  PROPELLER       CORRODED        B  EY2RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03                                                                    CORRODED HUB.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3O    NT3A13            5  CP3EA     
20060512000682006051200068GL  2006       5          12         79965            320060404G6114E71693          HUB                                     BEECH 58    58          1152740CE                                   HARTZLHCJ3Y PHCJ3YF2    GL  PROPELLER       CORRODED        B  EY2RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03                                                                    HUB CORRODED BEYOND REPAIR IAW MFG OVERHAUL MANUAL.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L72 3O      3A16            5  CP36EA    
20060224001582006022400158CE  2006       2          24         8862             120060115G324650107201        WHEEL                                   BEECH MU300 400A        1155402CE  PWA   JT15  JT15D5      52112NE                              LT MLG          MISOVERHAULED   B  YGJRC   ABORTED TAKEOFF                                                                                 W  INADEQUATE Q C                                                                TOTAKEOFF        1                      GL17234DK     24                RK182                                   LT MAIN TIRE DISINTEGRATED ON T/O ROLL. AFTER REMOVING WHEEL ASSY, DISCOVERED WHEEL HALVES O-RING EXPOSED BY VALUE STEM. UPON INVESTIGATION DISCOVERED WHEEL WAS NOT OVERHAULED IAW A/C BRAKING SYSTEMS COMPONENT MM.  INBOARD WHEEL HALF WAS NOT REMARKED IAW TEMPORARY REVISION NO. 32-6 TO COMPONENT MM MAIN WHEEL ASSY 5010720. UPON INVESTIGATION DISCOVERED THAT THE OTHER MAIN WHEEL INBOARD WHEEL WAS NOT REMARKED EITHER. THE SPARE WHEEL WHICH WAS OVERHAULED BY THE SAME REPAIR STATION WAS NOT MARKED EITHER.                                                                                                                                                                                                                       2H72 4F4  FRTA16SW   E25EA                
20060324000042006032400004CE  2006       3          24         8921             120060303G2897281810613       RELAY                                   LEAR  35    31          5170530CE                                                               FUEL PANEL      SHORTED         D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SW00XAJYC                       30                                      LEFT ENGINE WOULD NOT START.  TROUBLESHOT TO SHORTED RELAY ON FUEL RELAY PANEL.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F    RTA10CE                        
20060619002382006061900238EU  2006       6          19         AACSDR061006B    120060610G2150                LINE            AIRCOM                  AGUSTAA109  A119        0261102EU                                                               AIR CONDITIONER MAINT ERROR     B  DT1RK   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      EA17119RW                       14508                                   AIR CONDITIONING SYSTEM STC NR SR00463DE UTILIZES RIGID FREON LINES RUNNING FORE AND AFT ON THE ENGINE DECK.  AT THE FORWARD END, THESE LINES CONNECT TO FLEX LINES. AT THIS CONNECTION THE LINES WERE SWAPPED. THE CONNECTIONS ARE LOCATED RIGHT NEXT TO EACH OTHER AND THE LINES RUN PARALLEL, MAKING THIS A VERY EASY MISTAKE. THESE LINES SHOULD UTILIZE DIFFERENT FITTINGS TO PREVENT THIS FROM HAPPENING.                                                                                                                                                                                                                                                                                                                                 1G72 3U      H7EU                         
20070511001542007051100154SW  2007       5          11         AACSDR121406     120061214G53023P5340A11951    LONGERON                                AGUSTAAB139 AB139       0260110SW  PWA   PT6   PT6*        52043EA                              TAILBOOM        CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA17805HD                       31051                                   DURING INSPECTION OF THE TAILBOOM ATTACHMENT POINTS, A CRACK ABOUT 1.5 INCHES LONG WAS DISCOVERED ON THE TOP LT LONGERON AT STA 8700MM.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2G72 6U3  T  R00002RDE2NE                 
20060711001082006071100108    2006       7          11         AACSDR61006      120060610G53021090371231      LONGERON        AGUSTA                                                                                                                  TAILBOOM        CRACKED         B  DT1RO   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      EA1745HV 1900       A7093                                               DURING FLIGHT A BANG WAS HEARD, AIRCRAFT SHUDDERED MOMENTARILY, PILOT SUSPECTED BIRD STRIKE. FLIGHT CONTINUED TO LANDING SITE. AIRCRAFT WAS INSPECTED FOR DAMAGE, NO EVIDENCE OF BIRD STRIKE OR ANY DAMAGE WAS NOTED. DURING A SUBSEQUENT AIRFRAME INSPECTION LT UPPER TAILBOOM TO FUSELAGE FITTING WAS FOUND CRACKED.  A/C AND COMPONENT TOTAL TIME APPROXIMATELY 1900.0 HRS.                                                                                                                                                                                                                                                                                                                                                                                                            
20070511001522007051100152SW  2007       5          11         AACSDR61606      120060616G6510                DRIVE SHAFT                             AGUSTAAB139 AB139       0260110SW                                                               TAIL ROTOR      UNBONDED        B  DT1RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA17XA00113                     31047                                   NEW AIRCRAFT WAS BEING ASSEMBLED AFTER SHIPPING. DURING ASSEMBLY TAIL ROTOR DRIVESHAFT WAS FOUND SCORED AROUND UPPER FLANGE ATTACHMENT AREA. THIS WAS DIRECTLY BELOW THE TAILROTOR GEARBOX, AT THE TOP OF THE VERTICAL FIN.  SCORING WAS CAUSED BY A (CLICK-BOND) TYPE FASTENER/STANDOFF USED TO SECURE A WIRE HARNESS. THE FASTENER CAME UNBONDED FROM THE FUSELAGE AND ALLOWED THE WIRE HARNESS TO CONTACT THE DRIVESHAFT. THE CLAMP AND SCREW CAUSED THE SCORING ON THE DRIVESHAFT FLANGE.                                                                                                                                                                                                                                                   2G72 6U      R00002RD                     
20070108001382007010800138    2007       1          8          AFASVRA335       420061201G2562                G SWITCH        DORNEMARGLN                                                                                                             ELT             FAILED          D      K   NONE                                                                                            L  NO TEST                                                                       ININSP/MAINT     1                      NM03     9331       4959                                                ANNUAL INSPECTION TESTING OF ELT IAW AC 43.13-1B, CHAPTER 12, PARA 12-22C.   THE G-SWITCH WOULD NOT ACTIVATE. THE NORMAL ON FUNCTIONED SATISFACTORY.  WHEN THE ELT WAS AT ROOM TEMPERATURE, G-SWITCH FUNCTIONED PROPERLY BUT WHEN COLD SOAKED IN THE HANGER IT WOULD NOT ACTIVATE.  TRIED THE G-SWITCH NUMERIOUS TIMES AND IT WOULD NOT ACTIVATE WHEN COLD.  BATTERY EXPIRATION DATE MAR 2007.                                                                                                                                                                                                                                                                                                                                                                                            
20060518002692006051800269    2006       5          18         AMCR200600001    420060405G2562MN1300          BATTERY         ACK         E01         CIRRUSSR    SR22        2130001GL                                                               ELT             CORRODED        B  AMCRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL09679DV420        041133      0196                                    DURING ANNUAL INSP, ELT DID NOT TEST. FOUND 2 D-CELL BATTERIES CORRODED. THESE 2 BATTERIES WERE AT THE BOTTOM OF THE STACK AND THE CORROSION WAS NOT EVIDENT AT FIRST. THERE WERE 2 YEARS REMAINING BEFORE BATTERY REPLACEMENT WAS DUE. THESE ARE THE ORIGINAL BATTERIES SINCE NEW (APRIL 2002).  RECOMMEND BATTERIES BE REMOVED COMPLETELY AT EACH ANNUAL AND INSPECTED.                                                                                                                                                                                                                                                                                                                                                                       1L71 3O    NTA00009CH                     
20060926001282006092600128    2006       9          26         AMCR200600002    420060925G3414EA517245CES     INDICATOR                               CESSNA208   208B        2073701CE                                                               AIRSPEED        LEAKING         B  AMCRO   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      GL09479DV129                    208B1169                                PILOT REPORTED AN AIRSPEED SPLIT BETWEEN THE 2 INDICATORS. MAINTENANCE FOUND THE CO-PILOTS INDICATOR LEAKING INTERNALLY. FOUND INDICATOR TO BE AN OLDER, SUPERSEDED TYPE. LATEST UNIT IAW IPC INSTALLED. MFG P/N C661064-0237.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H71 3T      A37CE                        
20061115001782006111500178EU  2006       11         15         AMCR200600003    120061107G3244237K232         TIRE                                    BRAERODH125 BAE125800A  1500285EU  GARRTTTFE731TFE731*     01518WP                              MLG             LEAKING         B  AMCRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL09527AC                       NA0405                                  AFTER MOUNTING A NEW GOODYEAR TIRE ON AN AHA1814 WHEEL, THE TIRE FAILED THE 24 HOUR LEAK CHECK. EXCESSIVE VENTING WAS SEEN FROM MANY VENT HOLES IN THE BEAD AREA. TWO ADDITIONAL 24 HOUR CHECKS WERE PERFORMED AND LEAK RATE WAS ABOUT 19 PERCENT LOSS. AGAIN, EXCESSIVE LEAKING FROM VENT HOLES. TIRE RETURNED FOR WARRANTY.                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  FRTA3EU    E6WE                 
20061115003212006111500321NE  2006       11         15         AMCR200600004    120061113G79216454474         QUILL                                   SKRSKYS76   S76B        8143007NE  PWA   PT6   PT6*        52043EA                              BLOWER          WORN            B  AMCRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL09520AC     580   16471       760380                                  DURING A POSTFLIGHT INSPECTION, MECHANIC WIGGLED THE IMPELLER OF THE LT OIL COOLER BLOWER AND NOTICED EXCESSIVE PLAY AND PROCEEDED TO REMOVE THE BLOWER. INVESTIGATION REVEALED THE SPLINE SHAFT TEETH OF BOTH THE BLOWER'S QUILL SHAFT AND THE ACCESSORY DRIVE TO BE EXCESSIVELY WORN TO THE POINT THAT FAILURE WAS IMMINENT. THE SPLINE TEETH WERE DRY SO IT IS SUSPECTED THAT THE LUBRICATION WAS MISSED AT LAST INTERVAL. BUT THE REPLACEMENT OIL COOLER BLOWER, WITH AN OVERHAUL TAG, WAS FOUND TO HAVE IT'S IMPELLER INSTALLED UPSIDE DOWN. KUDO'S TO THE MECHANIC FOR THOROUGHLY CHECKING BOTH UNITS WITH UNCANNY ATTENTION TO DETAIL.                                                                                                   1G72 4U3  T  H1NE    E2NE                 
20060424001522006042400152NM  2006       4          24         AMTA200600279    120060414G2840                FUEL TANK                               BOEING737   73783N      13844HINM                                                               WING            READS HIGH      A  AMTAK   NONE                                                                                            O  OTHER                                                                         CRCRUISE         1                      GL11319TZ                       30643                                   RT MAIN FUEL TANK READ 400 LBS HIGH.  FQIS TEST SHOWS NO FAULT FOR RT MAIN TANK.  CHECK GOOD, C/W FIM 28-41-00-810.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F    RTA16WE                        
20060428001162006042800116CE  2006       4          28         AOC06001         120060316G323012806005        ACTUATOR        CESSNA      NA          CESSNA210   T210L       2073449CE                                                               NLG             BROKEN          B  R29RK   NONE                                                                                            O  OTHER                                                                         LDLANDING        1                      SW19579776593                   21061475                                UPON LANDING, THE NOSE LANDING GEAR COLLAPSED, CAUSING MAJOR DAMAGE TO THE PROPELLER AND DAMAGE TO THE NOSE SECTION OF THE AIRCRAFT.  INSPECTION AFTER RECOVERY REVEALED THE THE BEARING END (P/N - 1280600-5) HAD BROKEN, ALSO SHEARING THE PINS (P/N - 1280209-1).  NO EVIDENCE OF A PRE-EXISTING CRACK NOTED.  PARTS SENT TO CESSNA FOR EVALUATION.                                                                                                                                                                                                                                                                                                                                                                                          1H71 3O      3A21                         
20060413002572006041300257GL  2006       4          13         ASWFSDO15OKC     120060207G3233                ACTUATOR                                AMTR  GAIR  GLASAIRIII  05691HKGL                                                               NLG             WORN            C      K   NONE                                                                                            K  FLUID LOSS                                                                    LDLANDING        1                      SW99373R                                                                THE PILOT STATED THAT DURING ROLLOUT AFTER LANDING A HOME BUILT GLASAIR III HE APPLIED THE BRAKES AND THE NOSE GEAR COLLAPSED.  THE PILOT SAID THE LANDING GEAR POSITION INDICATOR LIGHTS WERE GREEN PRIOR TO LANDING.  THE NOSE GEAR ACTUATOR WAS FOUND TO BE LEAKING FLUID.  DURING DISASSEMBLY OF THE ACTUATOR THE PISTON SEAL WAS FOUND TORN.  THE AIRCRAFT OWNER SUSPECTS THAT HYDRAULIC FLUID WAS BY PASSING THE PISTON DURING OPERATION BECAUSE OF THE TORN SEAL.  THE ACTUATOR DID NOT PRODUCE ENOUGH FORCE TO OVERCOME THE AIR LOAD ON THE NOSE GEAR TO LOCK THE NOSE GEAR DOWN.  THIS IS THE SUBJECT OF STODDARD-HAMILTON SERVICE BULLETIN 136.                                                                                       1L71 3O    RTEXPA1L71                     
20060227000682006022700068NM  2006       2          27         AUCR200600001    120060201G57309006071         PANEL                                   LKHEEDP3A   P3A         5260103NM  ALLSN T56   T56A10      03004GL                              LT WING         CRACKED         B  AUCRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP25927AU16619                  151369                                  LT WING, STA. 82, 2.9 IN. FRACTURE IN NR 7 PLANK FORWARD TANG. FRACTURE WAS LOCATED BY ULTRASONIC INSPECTION DURING EVALUATION OF FUEL STAIN AT ANNUAL INSPECTION. THERE EXISTS AN APPROVED REPAIR FOR THIS DAMAGE IN THE SRM.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L74 4T4  TRTA32NM   E282                 
20060427001282006042700128NM  2006       4          27         AUCR200600002    120060321G57119010622         SPAR CAP                                LKHEEDP3A   P3A         5260103NM                                                               WING            CORRODED        B  AUCRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP25922A 12531                  151387                                  UPPER REAR SPAR CAP STRESS CORROSION CRACKED IN AFT RADIUS FORWARD OF NR 4 FLAP HANGER.  DAMAGE CENTERED AT WS275.  DAMAGE WAS INITIALLY DETECTED VISUALLY DURING SCHEDULED SPECIAL INSPECTION.  DAMAGE WAS FURTHER EVALUATED WITH EDDY CURRENT INSPECTION AND WAS FOUND TO EXCEED THE PARAMETERS OF THE SRM.  US TECHNICAL ENGINEERING HAS BEEN CONTRACTED TO GENERATE AN APPROVED REPAIR.                                                                                                                                                                                                                                                                                                                                                     2L74 4T    RTA32NM                        
20060512000842006051200084NM  2006       5          12         AUCR200600003    120060427G57309006051         PANEL                                   LKHEEDP3A   P3A         5260103NM                                                               RT WING         CRACKED         B  AUCRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP25925AU16997                  151361                                  CRACKED RISER, NR 4 FUEL TANK LOWER PLANK NR 4 AT NR 27 RISER WS397R.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L74 4T    RTA32NM                        
20060515002032006051500203NM  2006       5          15         AUCR200600004    120060427G57309006041         SKIN PANEL                              LKHEEDP3A   P3A         5260103NM                                                               LT WING         DAMAGED         B  AUCRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP25925AU16997                  151361                                  BOTTOM LT WING WS68.5, 4 FUEL BOOST PUMP SCREEN ATTACHING HOLES ELONGATED IN NR 17 AND NR 18 RISER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L74 4T    RTA32NM                        
20060612000462006061200046NM  2006       6          12         AUCR200600006    120060531G57119010621         SPAR CAP                                LKHEEDP3A   P3A         5260103NM                                                               LT WING         CRACKED         B  AUCRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP25900AU15902                  151391                                  DURING SCHEDULED INSPECTION FOUND CORROSION INDUCED CRACK IN UPPER AFT SPAR CAP EXTENDING OUTBOARD FROM PREVIOUS REPAIR IN THE AREA OF FLAP TRACK 5, WS 346.  DURING DISASSEMBLY TO EFFECT REPAIR FOUND ADDITIONAL STRESS CORROSION FRACTURE ON UPPER AFT SPAR CAP AT FLAP TRACK 4, WS 275.  THE AFFECTED AREAS RECEIVE A DETAILED INSPECTION ANNUALLY.                                                                                                                                                                                                                                                                                                                                                                                         2L74 4T    RTA32NM                        
20060512000732006051200073GL  2006       5          12         AVI000021        120060419G552011626002        ELEVATOR        CIRRUS      10146005    CIRRUSSR    SR22        2130001GL  CONT  O550  IO550*           SO                              ELEVATOR        OUT OF TOLERANCED      K   NONE                                                                                            OOOOTHER                     OTHER                     OTHER                     ININSP/MAINT     1                      SO15753CD796  796               0090                                    DURING SA 06-05 ELEVATOR GAP VISUAL INSPECTION IT WAS NOTED THAT THE GAP BETWEEN ELEVATOR TIP AND HORIZONTAL STABILIZER WAS LESS THEN 0.10 INCH, UPON FURTHER INVESTIGATION IT WAS NOTED THAT PN 11626-002 ELEVATOR HINGE, OB WAS RUBBING ON HORIZONTAL STABILIZER OB HINGE. ELEVATOR WAS RE-SHIMMED BY INSTALLING SHIM PN 11508-005.                                                                                                                                                                                                                                                                                                                                                                                                           1L71 3O3  ONTA00009CHE3SO                 
20060518002482006051800248CE  2006       5          18         B3OR20060111     120060419G2497                TERMINAL                                CESSNA500   550         2076604CE                                                               WIRING SYS      MISINSTALLED    B  B3ORD   RETURN TO BLOCK                                                                                 O  OTHER                                                                         TXTAXI/GRND HDL  1                      SW031200N                       5500681                                 WIRE TERMINAL WAS IMPROPERLY CRIMPED ONTO WIRE INSULATION WITH STRIPPED END OF WIRE STRANDS CONTACTING TERMINAL SCREW AT VOLTAGE METER CIRCUIT BREAKER.  THIS DISCREPANCY CAUSED AN INTERMITTENT VOLTAGE METER READING FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L72 4F      A22CE                        
20060214002162006021400216EU  2006       2          14         B3OR20060125     120060126G6510350A34021006    DRIVE SHAFT                             SNIAS 350   AS350B2     8680813EU                                                               TAIL ROTOR      MISOVERHAULED   B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW035204J                       3118                                    DURING ROUTINE TBO REPLACEMENT OF TAIL ROTOR DRIVESHAFT; IT WAS DISCOVERED THAT THE FORWARD END OF THE RECENTLY OVERHAULED REPLACEMENT WAS UNPAINTED CAUSING THE NR 5 BEARING FIT TOLERANCES TO BE TOO LOOSE.  MFG TECHNICAL REPRESENTATIVES VERIFIED THAT THE DRIVESHAFT IS SUPPOSED TO BE PAINTED UP TO THE SPLINES.  PART WAS RETURNED FOR FURTHER REWORK.                                                                                                                                                                                                                                                                                                                                                                                   1G71 3U      H9EU                         
20060127000672006012700067EU  2006       1          27         B3OR20060126     120060126G6510350A34021006    DRIVE ASSY                              SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1        NE                              TAIL ROTOR      MISOVERHAULED   B  B3ORK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW035204J                       3118        9318                        DURING ROUTINE TBO REPLACEMENT, DISCOVERED THE NEWLY OVERHAULED TAIL ROTOR DRIVESHAFT FORWARD END WAS UNPAINTED CAUSING AN UNSERVICEABLY LOOSE FIT OF THE NR 5 BEARING.  MANUFACTURER TECHNICAL REPRESENTATIVES VERIFIED THAT THE AREA IN QUESTION IS SUPPOSED TO BE PAINTED UP TO THE SPLINES.   PART WAS RETURNED FOR FURTHER REWORK.                                                                                                                                                                                                                                                                                                                                                                                                         1G71 3U3  U  H9EU    E19EU                
20070108001402007010800140CE  2007       1          8          BIOR061211001    120061211G5350101420024438    FAIRING                                 BEECH 200   B200        1152922CE  PWA   PT6   PT6A42      52043NE                                              CORRODED        B  BIORK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA23200MJ9672                   BB1012                                  DURING A PHASE 4 INSPECTION PAINT BLISTERS WERE NOTED ON THE LT AND RT WING ROOT FAIRING LOWER AFT PANELS P/N 101-420024-43 AND 101-420024-8. UPON FURTHER INSPECTION BOTH PANELS WERE FOUND TO BE CORRODED THRU IN SEVERAL PLACES FROM THE INSIDE OUT.  AFTER REMOVING THE PANELS IT WAS DISCOVERED THAT THE ACOUSTIC FOAM HAD BECOME SOAKED WITH WATER OVER TIME. THIS SET UP CORROSION OVER THE ENTIRE AREA OF THE INSIDE OF BOTH PANELS. ALSO WHERE THIS MATERIAL CONTACTED THE FUSELAGE ON THE LT SIDE IT CAUSED CORROSION THRU THE PRESSURE VESSEL.  MFG HAS BEEN NOTIFIED AND SUPPLIED WITH PHOTO DOCUMENTATION.                                                                                                                         1L72 4T4  T  A24CE   E4EA                 
20061204000042006120400004WP  2006       12         4          BS2R2120003      120061117G6310269A5472        PULLEY BRACKET  HUGHES                  HUGHES269   269C        4470504WP  LYC   O360  HIO360D1A   41514EA                              BELT DRIVE SYSTEBROKEN          B  BS2RCE  ABORTED TAKEOFF         ENGINE SHUTDOWN                                                         R  PARTIAL RPM/PWR LOSS                                                          TOTAKEOFF        1                      SW17110472701 29                211031      L2209551A                   ONE OF THE TWO BELT DRIVE CLUTCH ACTUATOR CABLE PULLEY BRACKETS BROKE CLEAN ACROSS BETWEEN THE FRAME MOUNT HOLE AND THE PULLEY MOUNT HOLE DURING ENGAGEMENT OF THE ROTOR SYSTEM. DURING THE SUBSEQUENT TAKE OFF ATTEMPT THE ROTOR RPM WOULD BLEED OFF RAPIDLY DUE TO DRIVE BELT SLIPPAGE ANY TIME THE M/R COLLECTIVE CONTROL WAS RAISED.THE AICRAFT WAS SHUT DOWN AND THE PROBLEM INVESTIGATED BY THE OPERATOR THEN MAINTENANCE PERSONELL WERE NOTIFIED.                                                                                                                                                                                                                                                                                        1G71 3O3  O  4H12    1E10                 
20060614000702006061400070EA  2006       6          14         CA060103001      220060102G7230                ENGINE                                  BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA  HARTZLHCD4N3HCD4N3A     GL  RIGHT           FAILED          W      A   UNSCHED LANDING                                                                                 RXJPARTIAL RPM/PWR LOSS      ENGINE FLAMEOUT           WARNING INDICATION        DEDESCENT        1                      CA                                          PCE81119                    AT APPROXIMATELY 09:30 THIS MORNING, THE RT ENGINE OF KING AIR 200 HAD AN IN-FLIGHT TORQUE ROLL BACK TO APPROX 200 FT LBS, WITH A RISE IN ITT TO APPROX 680 DEG C, WITH A POPPING NOISE AND CORRESPONDING FLAMES FROM THE RT ENGINE EXHAUST.  THE CREW INITIATED THE ENGINE SHUTDOWN.                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L72 4T4  T  A24CE   E4EA    5  CSTC      
20060615000272006061500027EU  2006       6          15         CA060104004      120060102G561001379377C405    WINDSCREEN                              BAG   JETSTMJETSTM3212  1500217EU  GARRTTTPE331TPE33110UG  01514WP  ROTOL R333  R333482F12  GL  COCKPIT         CRACKED         W      BA  EMER. DESCENT           UNSCHED LANDING                                                         A  FLAME/FIRE                                                                    CRCRUISE         1                      CA                                                                      AT CRUISE ALT 20,000 FT, NOTICED CRACK AND SUBSEQUENT FLAME WITHIN LAYERS OF LT WINDSHIELD.  FLAME SELF EXTINGUISHED WITH DE-SELECTION OF WINDSHIELD HEAT.  DURING DESCENT ADDITIONAL CRACKING.  DIVERTED TO CYMM.  MX DISPATCHED, REPLACED WINDSHIELD.  UPON MX REVIEW FOLLOWING WAS DETERMINED; THE PART WAS IN SERVICE ON THIS A/C ON REGISTER SINCE 2003 JANUARY AND PRIOR.  NO ABNORMALITIES OBSERVED DURING REMOVAL REGARDING INSTALLATION, EXCEPT FOR PRC APPLIED OVER EXT SCREW HEADS.  AIRFRAME VOLTAGE AND CURRENT OUTPUT TO LT WINDOW HEAT SYS FOUND NORMAL.  NO EVIDENCE OF MISTORQUE OF SECURING SCREWS OBSERVED.  MX PRELIMINARY CONCLUSION, MALFUNCTION LEADING TO A SHORT CIRCUIT OF INTERNAL HEAT FILAMENTS OF WINDSHIELD.     2L72 4T4  TRTBA15CAA E4WE    6  CP61GL    
20060615001422006061500142EU  2006       6          15         CA060104005      120060104G2530820317000       OVEN                                    AIRBUSA330  A330*              EU  RROYCERB211 RB211*      54555NE                              FWD GALLEY      SHORTED         W      F   ACTIVATE FIRE EXT.                                                                              A OFLAME/FIRE                                          OTHER                     CRCRUISE         1                      CA                                                                      FWD GALLEY OVEN FIRE EXTINGUISHED WITH 2 FIRE EXT BOTTLES ACTION.  FWD GALLEY NR1/NR 2 OVENS REPLACED. FUNCT CHKD SERV  NR 1 OFF HK76R5  NR 2 OFF 8203-17-000 S/N 9403-6150.  NR 1 ON 8203-17-000, S/N 96-11-7934 NR 2 ON 568K81.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F4  FRTA46NM   A12EU                
20060615001792006061500179EU  2006       6          15         CA060104007      120060104G3260201122006       UPLOCK                                  AIRBUS320   A320211     3930320EU  CFMINTCFM56 CFM565A1         NE                              MLG             DAMAGED         W      O   OTHER                                                                                           J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      AFTER T/O ECAM L/G DOORS NOT CLOSED.  CYCLED LDG GEAR.  ECAM RE-APPEARED.  LT MAIN GEAR DOOR SHOWED PARTIALLY OPEN IN AMBER.  GEAR DOORS SHOW CLOSED WHEN GEAR DOWN.  LT GEAR DOOR UPLOCK ASSY REPLACED AS PER TASK, 32-31-33-400-002.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA28NM   E29NE                
20060615001812006061500181NE  2006       6          15         CA060104008      220060104G75300CFM565A5       REDUCER                                 AIRBUSA319  A319114     3930350NM  GE    CFM56 CFM565A     13802NE                              P3 LINE         SHEARED         W      E   ENGINE SHUTDOWN                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      IN CLIMB THRU FL185, ENG NR 2 PWR REDUCED TO 74.5 N1/1200 KGH FF.  ENG PARAMETERS NORMAL WHEN PWR REDUCED TO LOWER SETTINGS.  ENG NR 1 NORMAL THROUGHOUT.  FOUND PS3 LINE REDUCER SHEARED AS PER TSM 77-00-00-810-833.  REDUCER REPLACED AS PER AIRBUS STANDARD PRACTICES.  GROUND RUN CHKD SERV.                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F4  FRTA28NM   E29NE                
20060615001822006061500182SW  2006       6          15         CA060104009      120060104G79212660163501      SHAFT           BELL                    BELL  212   212         1181420SW  PWA   PT6T  PT6T3       52045EA                              BLOWER          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       8292 582   30791                                               PERFORMED MAGNETIC PARTICLE INSPECTION IAW BHT-ALL-SPM, SHAFT P/N 2660-1635-01 WAS FOUND TO BE CRACKED IN KEY WAY, PART HAS BEEN SUBSEQUENTLY SCRAPED.  BELL HELICOPTER HAS BEEN NOTIFIED FOR INTEREST AND INFORMATION ONLY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1G71 4U4  U  H4SW    E22EA                
20060615001832006061500183    2006       6          15         CA060104010      420060101G233050401100003     VIDEO DISPLAY                           BOEING737   737*               NM  CFMINTCFM567CFM567B22   13802NE                              SEAT 20E        ODOR            W      H   DEACTIVATE SYST/CIRCUITS                                                                        B  SMOKE/FUMES/ODORS/SPARKS                                                      DEDESCENT        1                      CA                                                                      A/C WAS ON DESCENT WHEN A BURNING SMELL WAS NOTICED COMING FROM SEAT 20E VDU.  THE IFE SYSTEM WAS DEACTIVATED.  MAINTENANCE REPLACED THE VDU AND THE SYSTEM WAS TESTED SERVICEABLE.  THIS COMPONENT WILL BE RETURNED TO THE MANUFACTURER AND A COMPLETE TEAR DOWN REPORT WILL BE REQUESTED.                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA16WE   E00055EN             
20060615001842006061500184SW  2006       6          15         CA060104011      120060102G561027194423REV3    WINDSHIELD                              FRCHLDSA227 SA227DC     3377521SW  GARRTTTPE331TPE33112UHR      WP  MCAULY4HFR344HFR34C652  NE  COCKPIT         CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA                                                                      LT WINDSHIELD CRACKED WHILE AT FL250.  CREW CARRIED ON TO BASE AT LOWER ALTITUDE AND SLOWER AIRSPEED.  MAINTENANCE IS CHANGING WINDSHIELD.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4T4  TRTA18SW   E4WE    6  C3PNE     
20060615001852006061500185    2006       6          15         CA060105001      420060103G233050401100003     VIDEO DISPLAY                           BOEING737   737*               NM  CFMINTCFM567CFM567B22   13802NE                              SEAT 6D         SMOKE           W      H   DEACTIVATE SYST/CIRCUITS                                                                        B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA                                                                      A/C WAS IN CRUISE WHEN SMOKE WAS OBSERVED COMING FROM SEAT 6D VDU.  THE IFE SYSTEM WAS DEACTIVATED.  MAINTENANCE REPLACED THE VDU AND THE SYSTEM WAS TESTED SERVICEABLE.  THIS COMPONENT WILL BE RETURNED TO THE MANUFACTURER AND A COMPLETE TEAR DOWN REPORT WILL BE REQUESTED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F4  FRTA16WE   E00055EN             
20060615002032006061500203CE  2006       6          15         CA060105004      120060105G3246NIL             CONTROL CABLE                           CESSNA206   206H        2073301CE  LYC   O540  IO540AC1A5       EA  HARTZLHCF3Y HCF3YR1     GL  WATER RUDDER    FRAYED          W      K   NONE                                                                                            OK OTHER                     FLUID LOSS                                          ININSP/MAINT     1                      CA       1065                                                           WATER RUDDER STEERING CABLES ARE FRAYED WHERE IT ENTERS THE SIDE OF THE FLOAT.  THE MAIN CAUSE OF THIS IS A MISALIGNMENT OF THE HOLE ON THE SIDE OF THE FLOAT TO THE ACTUAL POSITIONING OF THE RUN.  IN SOME CASES, THE CABLE HAD CUT A 1/4" SLOT ON THE FLOAT SIDE SKIN DUE TO THIS MISALIGNMENT.                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O3  ORTA4CE    1E4     5  CP31EA    
20060724000762006072400076WP  2006       7          24         CA060106001      220060101G7200                ENGINE                                  BOMBDRBD700 BD7001A10   1390006GL  HNYWL AS907 AS90711A    33908WP                              LEFT            MALFUNCTIONED   W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         O  OTHER                                                                         CLCLIMB          1                      CA                                          3030014                     (CAN) ON CLIMB OUT CREW REPORTED A LOUD THUMP FOLLOWED BY A DROP IN LT ENGINE OIL PRESSURE AND AN AIRFRAME VIBRATION. CREW SHUT DOWN THE ENGINE DELARED AN EMERENCY AND RETURNED TO AIRPORT.  LT ENGINE REMOVED AND LOANER INSTALLED. (TC NR 20060106001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F4  FRTT00003NYE00010LA             
20060616000512006061600051CE  2006       6          16         CA060106003      120060105G3297                WIRE                                    BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE                              UPLOCK SWITCH   DAMAGED         W      O   OTHER                                                                                           O  OTHER                                                                         APAPPROACH       1                      CA                                                                      UPON ARRIVAL, THE GEAR WAS SELECTED DOWN BUT NO DOWN AND LOCKED ANNUNCIATORS ILLUMINATED.  THE IN TRANSIT LIGHT WAS ALSO NOT ILLUMINATED SO THE PILOT DID A FLY BY OF TOWER TO CONFIRM GEAR POSITION, THEY ALSO HAD EMERGENCY SERVICES ON STANDBY.  AN UNEVENTFUL LANDING WAS COMPLETED.  AS THE AIRCRAFT WAS BEING SHUTDOWN THE CREW NOTICED THAT THE CB FOR THE ANNUNCIATORS WAS POPPED.  RESET THE CB AND ALL THE ANNUNCIATORS ILLUMINATED AS REQUIRED.  A SPECIAL FERRY PERMIT WAS ISSUED TO RETURN THE AIRCRAFT TO A MAINTENANCE BASE.  MAINTENANCE FOUND A CHAFED WIRE ON THE HARNESS FOR THE RT UPLOCK MICROSWITCH.  GEAR SWUNG AND AIRCRAFT RETURNED TO SERVICE.                                                                        2L72 4T4  TRTA24CE   E26NE                
20060616000522006061600052CE  2006       6          16         CA060106004      120060105G561010138402523     WINDSHIELD                              BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE  HARTZLHCE4A HCE4A3I     NE  COCKPIT         CRACKED         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA            1234                                                      DEPARTING AIRPORT THE LT HEATED WINDSHIELD CRACKED.  TURNED AROUND AND MADE AN UNEVENTFUL LANDING.  THE AIRCRAFT WAS SENT TO MAINTENANCE WHO REPLACED THE WINDSHIELD.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4T4  TRTA24CE   E26NE   5  CP10NE    
20060616000532006061600053EA  2006       6          16         CA060108001      120060104G5610NP1393216       WINDSHIELD                              CNDAIRCL600 CL6002C10   1390015EA  GE    CF34  CF343B1          NE                              COPILOT'S       CRACKED         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA                  99307H2825                                          RIGHT WINDSHIELD CRACKED DURING CLIMB.  DIVERTED FLIGHT BACK TO DEPARTURE AIRPORT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F4  FRTA21EA   E15NE                
20060616000542006061600054EA  2006       6          16         CA060108002      120060103G5610NP1393211       WINDSHIELD                              CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                                              CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         APAPPROACH       1                      CA                                                                      DURING APPROACH, THE LEFT WINDSHIELD CRACKED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  FRTA21EA   E15NE                
20060616000562006061600056WP  2006       6          16         CA060109001      120060103G6730D2121           SERVO                                   ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              HYDRAULIC       LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       92                                                             DURING DAILY INSPECTION, NOTICEABLE AMOUNT OF HYDRAULIC FLUID LEAKING FROM SERVO.  GROUND RUN DETERMINED PILOT VALVE SOURCE OF LEAK.  AFT SERVO REMOVED AND RETURNED TO ROBINSON HELICOPTERS FOR WARRANTY REPAIRS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1G71 3O3  O  H11NM   1E4                  
20060616000572006061600057NM  2006       6          16         CA060109002      120060106G3297471515          WIRE HARNESS                            BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                              NLG WOW         DAMAGED         W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      CA                                                                      AIR TURN BACK DUE TO NR 2 WOW CAUTION LIGHT.  NLG WOW 2 HARNESS REPLACED.  AIRCRAFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2H72 4T4  TRTA13NM   E00062EN             
20060616000602006061600060CE  2006       6          16         CA060110001      120060106G33102K40D10         RESISTOR                                BEECH 90    C90A        1152911CE  PWA   PT6   PT6A21      52043EA  HARTZLHCB3T HCB3TN3     GL  PANEL LIGHT     OVERHEATED      W      K   NONE                                                                                            M  OVER TEMP                                                                     ININSP/MAINT     1                      CA                                                                      DURING SPECIAL INSPECTION AS PER CAMPAIGN 681-33-21-018, FOUND RESISTOR R145 (ATA 33-21-01 PAGE 4) OVERHEATED.  INSULATION ABOVE THE RESISTOR WAS SCORCHED AND BURNED.  THE SYSTEM WAS DEACTIVATED AND DEFERRED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L72 3T4  TRT3A20    E4EA    6  CP15EA    
20060616000622006061600062NM  2006       6          16         CA060110002      120060108G7933MS280344        PROBE                                   DHAV  DHC8  DHC8201     2809001NM  PWA   120   PW123D      52152NE  HAMSTD14SF  14SF23      NE  OIL TEMPERATURE MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CRCRUISE         1                      CA       18748                                                          DURING CRUISE, THE LT OIL TEMPERATURE INDICATION WAS NOTICED TO BE INTERMITTENTLY FLUCTUATING AND UNSERVICEABLE.  CREW ELECTED TO RETURN THE AIRCRAFT TO BASE WHERE AN APPROACH AND LANDING WAS CARRIED OUT WITHOUT INCIDENT.  ENGINEERING INVESTIGATION REVEALED THAT THE ENGINE'S OIL TEMPERATURE PROBE WAS UNSERVICEABLE.  THE PROBE IN QUESTION WAS REPLACED AND FOLLOWING REQUIRED ENGINE RUNS AND CHECKS THE AIRCRAFT WAS RELEASED BACK TO SERVICE WITHOUT FURTHER INCIDENT.                                                                                                                                                                                                                                                              2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060616001082006061600108CE  2006       6          16         CA060110003      120060106G33102K40D10         RESISTOR                                BEECH 90    C90A        1152911CE  PWA   PT6   PT6A21      52043EA  HARTZLHCB3T HCB3TN3     GL  PANEL LIGHTS    OVERHEATED      W      K   NONE                                                                                            M  OVER TEMP                                                                     ININSP/MAINT     1                      CA                                                                      DURING SPECIAL INSPECTION AS PER CAMPAIGN 681-33-21-018, FOUND RESISTOR R145 (ATA 33-21-01 PAGE 4) OVERHEATED.  INSULATION ABOVE THE RESISTOR WAS SCORCHED AND BURNED.  THE SYSTEM WAS DEACTIVATED AND DEFERRED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L72 3T4  TRT3A20    E4EA    6  CP15EA    
20060616001152006061600115EA  2006       6          16         CA060110004      120060106G3244362K821         TIRE                                    CNDAIRCL600 CL600*             EA  GE    CF34  CF34*            NE                              NR 2            SEPARATED       W      O   OTHER                                                                                           DJ INFLIGHT SEPARATION       WARNING INDICATION                                  CLCLIMB          1                      CA       1160 504                                                       ON TAKEOFF, THE NR 2 MAIN TIRE RECAP DEPARTED THE TIRE CAUSING DAMAGE TO MLG SIDE STAY SPRINGS AND RETAINING PINS, INBD FLAP AND VANE, THE WING LOWER SKIN AFT OF THE LT GEAR BAY, AND THE INBD SPOILER FITTING ASSEMBLY.  SIGNS OF FOD NOTED IN THE LT ENGINE BUT DETAILED INSPECTION AND BOROSCOPE SHOWED NO DAMAGE SUSTAINED.  MAIN TIRE PRESSURES NOTED AS FOLLOWS NR 1 198 PSI, NR 2 140 PSI, NR 3 198 PSI, NR 4 198 PSI, S/N (D) IS TIRE SERIAL NUMBER NOT ASSEMBLY, RECAPPED AT WILKERSON.                                                                                                                                                                                                                                               2L72 4F4  FRTA21EA   E15NE                
20060616001162006061600116NE  2006       6          16         CA060110005      220060104G7230311074102       SHROUD                                                                     PWA   PT6   PT6A114A    52043NE                              COMPRESSOR      DISTORTED       W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       746                                PCE19201                    DURING A RECTIFICATION INSPECTION OF RENTAL ENGINE, CT SHROUD SEGMENT RETAINING RING OF POST SB 1627 CONFIG FOUND LOOSE AND MINOR SHIFTING OF CT SHROUD SEGMENT WAS NOTED.  CT SHROUD SEGMENT-RETAINING RING WAS OF POST SB 1627 CONFIG AND CT SHROUD SEGMENTS (P/N 3053094) WERE PER SB 1628.  QTY 6-RUB SPOTS WERE NOTED ON CT SHROUD SEGMENTS WITH MINOR RUB ON CT BLADES.  CT SHROUD SEGMENT-RETAINING RING WAS FOUND DISTORTED AND PARTIALLY DISENGAGED FROM RETAINING GROOVE OF CT SHROUD HOUSING.  NO OVER HEATING/BURNING OF HOT SECTION PARTS NOTED.  INSPECT OF CT SHROUD HOUSING WAS DONE AND ROUNDNESS OF ALL CRITICAL DIAMETERS NOTED WITHIN O/H MANUAL LIMIT.  SHIFTING OF CT SHROUD SEGMENTS WAS DUE TO PARTIAL DISENGAGEMENT OF        3  T          E4EA                 
20060627000032006062700003    2006       6          27         CA060110006      120060110G273082700561003     CABLE                                                                                                                                   ELEVATOR        DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      DURING CHECK , 2 CHAIN CABLE ASSY`S, P/N 82700561-003, TITLED "ELEV TRIM AND ELEV GUST LOCK CONTROL" INSPECT OF CHAINS, REF AD CF-2005-38, WAS FOUND INCORRECTLY ASSEMBLED AND SUPPLIED BY SPARES.  ASSY FOUND INCORRECTLY BUILT WHEN ATTEMPTING TO INSTALL AS PER AMM 27-36-01, PARA B, STEP 3.  SPECIFIES THAT CHAIN PLATE IS REQ`D TO BE ON INBD SIDE OF SPROCKET.  THIS CAN'T BE ACCOMP WITH NEW CHAIN ASSY IN ITS PRESENT CONFIG (DWG 82700561 SHOWS THE DIMENSIONS AND CORRECT ORIENTATION OF ASSY).   TECH HELP DESK E-MAILED, ADVISED OF ISSUE & REQUESTED TO PULL THEIR DRAWINGS TO CONFIRM OUR FINDINGS.  REQUESTED INSPECT EXISTING INVENTORY TO CONFIRM IF THEIR SPARES WERE ALSO AFFECTED.  REPLACEMENT CHAIN CABLE ASSY`S ORDERED                                           
20060616001172006061600117NM  2006       6          16         CA060110007      120060110G25308201170000      OVEN                                    AIRBUSA319  A319114     3930350NM  GE    CFM56 CFM565A     13802NE                              AFT GALLEY      SHORTED         W      O   OTHER                                                                                           A  FLAME/FIRE                                                                    CRCRUISE         1                      CA                                                                      OVEN NR 02-02-17535 OVEN NR 3 IN AFT GALLEY EMITTED AN ELECTRIC SHOCK TO F/A UPON TOUCHING IT.  MEL ERASED IN CCS AND CB PULLED AND COLLARED BY FLIGHT CREW.  REPLACED NR 3 OVEN CONTROLLER FUNCTION CHECK SATISFACTORY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F4  FRTA28NM   E29NE                
20060616001182006061600118    2006       6          16         CA060111001      120060103G2400                CIRCUIT BREAKER                                                                                                                                         BURNED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      AIRCRAFT HAD NR 1 AC GENERATOR INOPERATIVE (GOES OFFLINE AFTER 20 SECONDS).  INITIALLY, THE GENERATOR HAD BEEN REPLACED, HOWEVER, THE DISCREPANCY REMAINED.  SUBSEQUENTLY, CIRCUIT BREAKER, P/N 2TC2-5 FOUND WITH HOLE BURNT IN THE SIDE.  FOR RECTIFICATION PURPOSES, CONTACTOR RELAY 2421-K1 REPLACED.  RING CONNECTORS TO CB3 AND CB5 REPLACED, P/N HC-AJN022 (CONTACTOR RELAY), P/N 2TC2-5 (CB3) & (CB5).                                                                                                                                                                                                                                                                                                                                                                             
20060616001202006061600120NM  2006       6          16         CA060111002      120060111G534069215313        BRACKET                                 BOEING737   737522      138449FNM  CFMINTCFM56 CFM563C1    13802EU                              FUSELAGE        SPLIT           W      O   OTHER                                                                                           O  OTHER                                                                         LDLANDING        1                      CA                                                                      ON LANDING IN YYZ,FORWARD ATTENDANTS SEAT BELT CAME FREE OF THE ATTACH BRACKET.  UPON INVESTIGATION IT WAS FOUND THAT A WASHER WAS MISSING FROM THE RETAINING BOLT.  THIS MISSING WASHER WAS LEFT OFF THE BOLT AT INSTALLATION BY A PREVIOUS OPERATOR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA16WE   E21EU                
20060616001222006061600122GL  2006       6          16         CA060112001      220060107G72406870992         COMBUSTION CASE                         BOLKMS105   BO105S      5626006EU  ALLSN 250C  250C20B     03013GL                              ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      CREW REPORTED ABNORMALLY HIGH TOT ON NR 1 ENGINE.  INVESTIGATION REVEALED A CRACK IN THE RT ARMPIT AREA OF THE OUTER COMBUSTION CASE.  THE OUTER COMBUSTION CASE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1G72 3U3  U  H3EU    E4CE                 
20060616001232006061600123WP  2006       6          16         CA060112002      120060111G6730D2121           SERVO                                   ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              ROTOR FLT CONTROLEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       503                                                            HYDRAULIC LEAK FROM SERVO.  SERVO REMOVED FOR REPAIR AND REPLACED WITH SERVICEABLE UNIT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1G71 3O3  O  H11NM   1E4                  
20060616001242006061600124EA  2006       6          16         CA060112003      120060111G2540601R40467239    INSULATION                              CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                                              BURNED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       15193                                                          BURNT INSULATION BLANKET FOUND IN CARGO UNDERFLOOR AREA ON RT SIDE OF AIRCRAFT AROUND HEATED LAV WATER SERVICE PORT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F4  FRTA21EA   E15NE                
20060616001252006061600125WP  2006       6          16         CA060112004      120060111G6700C12131          PUSH-PULL ROD                           ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              MAST            WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       503                                                            WHILE REMOVING A HYDRAULIC SERVO, IT WAS NOTED THAT THE PUSH PULL TUBE FROM THE SERVO TO THE SWASHPLATE WAS WEARING WHERE IT PASSED THROUGH THE MIDDLE RIB OF THE MAST FAIRING.  THE CHAFING WAS MINOR, AND HAD ONLY GONE THOUGH THE TOP LAYER OF PAINT, AND STARTED ON THE PRIMER.  THE ENGINEERS SUSPECT THAT THE LOWER RIBS OF THE MAST WERE NOT CENTERED PROPERLY DURING MANUFACTUER, AND WERE ALTERING THE POSITION OF THE MIDDLE RIB.                                                                                                                                                                                                                                                                                                     1G71 3O3  O  H11NM   1E4                  
20060616001502006061600150SW  2006       6          16         CA060112005      120060110G52802755001177      DOOR                                    SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP                              LANDING GEAR    JAMMED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            DEDESCENT        1                      CA                                                                      DURING APPROACH, CREW ATTEMPTED TO EXTEND L/G AND NOTICED RT MAIN WAS NOT DOWN AND LOCKED.  IT WAS DETERMINED LANDING GEAR WAS NOT COMING OUT OF RT W/W.  IT TOOK SEVEN ATTEMPTS TO GET LANDING GEAR TO COME DOWN AND LOCK INTO POSITION.  INSPECTION REVEALED RT I/B GEAR DOOR HINGES WERE WORN, ALTHOUGH NOT EXCESSIVE, THAT TWO RT MLG DOORS OVERLAPPED DURING RETRACTION AND DID NOT ALLOW GEAR TO COME DOWN OUT OF W/W WHEN IT WAS EXTENDED FOR LANDING.  INSPECTION OF DOOR REVEALED SOME DENTS AND TEARING OF SKIN EDGE ON DOOR WHERE L/G GEAR WAS HITTING DOOR DURING ATTEMPTS TO EXTEND LANDING GEAR.  LANDING GEAR DOOR WAS REPLACED AND DOOR AND GEAR RIGGING CHECKED.  AIRCRAFT HAS SINCE RETURNED TO SERVICE.                      2L72 4T4  TRTA8SW    E4WE                 
20060619000692006061900069GL  2006       6          19         CA060112006      220060105G72506886407         TURBINE BLADES                                                             ALLSN 250C  250C*            GL                              ENGINE          BROKEN          W      ED  ENGINE SHUTDOWN         RETURN TO BLOCK                                                         CW F.O.D.                    INADEQUATE Q C                                      TXTAXI/GRND HDL  1                      CA       120                                CAT32511P                   TURBINE RECEIVED AT ESSENTIAL TURBINES IN A DISASSEMBLE STATE.  LOG CARDS REFLECT THAT THE TURBINE HAD BEEN INVOLVED IN A HARD LANDING.   IT HAD BEEN INSPECTED AND SENT TO MAC-V AVIATION WHO RE-ASSEMBLED THE ENGINE.  MAC-V STATED VIA A PHONE CALL THAT THE HARDWARE WAS MIXED IN THE COMBUSTION SECTION AND COULD NOT FIND ALL OF THE NUTS, BOLTS ETC.  OUR INVESTIGATION LEADS US TO BELIEVE THAT THE HARD LANDING WAS NOT A FACTOR.  THE FAILED TURBINE WHEEL WILL BE FORWARDED TO THE SAFETY BOARD TO EVALUATE THE REASON FOR FAILURE, POSSIBLY DUE TO FOD FROM ITEM MISSED DURING RE-ASSEMBLY.                                                                                                                                                3  U          E4CE                 
20060619000722006061900072CE  2006       6          19         CA060112007      120060101G5340                INTERCOSTAL                             CESSNA402   402C        207590RCE  CONT  O520  TSIO520VB   17040SO  MCAULY3AF32C3AF32C505   GL  RUDDER PEDAL    DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      PILOTS OUTBOARD INTERCOSTAL RUDDER PEDAL MOUNT REPAIRED DUE TO SEVERAL SMALL CRACKS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L72 3O3  O  A7CE    E8CE    5  CP22EA    
20060619000772006061900077SW  2006       6          19         CA060112009      120060112G77122719158007      INDICATOR                               FRCHLDSA227 SA227CC     3377522SW  GARRTTTPE331TPE33111U   01514WP  MCAULY4HFR344HFR34C652  NE  TORQUE          INOPERATIVE     W      C   ABORTED TAKEOFF                                                                                 N  FALSE WARNING                                                                 TOTAKEOFF        1                      CA                                                                      ON TAKEOFF, THE TORQUE INDICATOR WENT TO ZERO.  TAKEOFF ABORTED AND AIRCRAFT RETURNED TO BLOCKS.  MAINTENANCE REPLACED INDICATOR AND RELEASED AIRCRAFT AFTER SATISFACTORY GROUND RUN.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4T4  TRTA18SW   E4WE    6  C3PNE     
20060619002452006061900245WP  2006       6          19         CA060112010      120060108G801172566           RING GEAR                               ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              STARTER         DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       201                                                            STARTER RING GEAR REPLACED AFTER 201.1 HOURS.  MISSING TEETH.  AIRCRAFT TOTAL TIME 441.3.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1G71 3O3  O  H11NM   1E4                  
20060619002462006061900246WP  2006       6          19         CA060112011      120060105G2913D5001           PUMP                                    ROBSINR44   R44         7640120WP  LYC   O540  O540F1B5    41532EA                              HYD SYS         CONTAMINATED    W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       42                                                             DURING GROUND CHECK, THE PILOT NOTED PROBLEMS WITH FLIGHT CONTROL CHECK WITH HYDRAULICS.  MAINTENANCE FOUND FERROUS DEBRIS IN THE FILTER.  THE HYDRAULIC PUMP WAS REPLACED, AND SYSTEM FLUSHED.  NO FURTHER DEFECTS FOUND.  PUMP WAS SENT BACK TO MFG.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1G71 3O3  O  H11NM   E295                 
20060619002482006061900248EA  2006       6          19         CA060112013      120060108G5610NP1393219       WINDSHIELD                              CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              COCKPIT         CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA       9835                                                           LT WINDSHIELD FOUND CRACKED BEFORE FLIGHT.  LT WINDSHIELD REPLACED AND TESTED IAW TO AMM PROCEDURE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F4  FRTA21EA   E15NE                
20060619002492006061900249EU  2006       6          19         CA060116001      120060112G2910HTE400005       VALVE                                   BAG   JETSTMJETSTM3212  1500217EU  GARRTTTPE331TPE33110UG  01514WP  MCAULY4HFR344HFR34C652  NE  RT HYD SYSTEM   CRACKED         W      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  APAPPROACH       1                      CA       2012620126                                                     ON APPROACH, UPON FLAP SELECTION, NO SYSTEM HYD PRESSURE.  EMERG GEAR SELECTION USED TO EXTEND L/G, AND TO OBTAIN 10 DEGREES FLAP.  A/C LANDED W/O INCIDENT, DUE TO LOSS OF SYS HYD PRESSURE, N/W STEERING INOP AND MAIN BRAKING WAS LIMITED.  TOWED TO HANGAR.  MX FOUND PN HTE400005 CHECK VALVE CRACKED, WHICH RESULTED IN LOSS OF SYS HYD FLUID.  CHECK VALVE WAS REPLACED, SYS WAS REPLENISHED AND BLED, OPS CHECKED SERVICEABLE.  COMPANY ISSUED FLEET INSP TO DETERMINE IF A COMMON PROBLEM WITH FACTORY INSTALLATION.  FOUND MULTIPLE A/C WITH THESE NRV'S CRACKED IN RADIUS.  (FPI,  10X MAG. GLASS REQUIRED TO DETECT.)  VALVE'S REPLACED AS REQ`D AND MFG TO BE CONTACTED.  DEFECTIVE VALVES TAGGED AND ON FILE FOR FURTHER INSPECT. 2L72 4T4  TRTBA15CAA E4WE    6  C3PNE     
20060619002502006061900250GL  2006       6          19         CA060116002      220060116G726023069576        BEARING                                 EMB   145   EMB145      3260210SO  ALLSN AE300 AE3007A          GL                              ENGINE          FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       12348                              CAE311908                   ENGINE CAE311908 CAME IN THE SHOP FOR METAL DEBRIS IN THE FILTER.  DURING ENGINE DISASSEMBLY IT WAS FOUND THAT NR 6 MID SPAN BEARING ASSEMBLY HAD FAILED.  MID-SPAN BEARING OUTER RACE WAS STILL IN ITS HOUSING AND ONLY 3 ROLLERS AND A PIECE OF BEARING CAGE WERE FOUND.  THE RADIAL DRIVE QUILL SHAFT WAS FOUND BROKEN ABOVE THE SPLINES CONNECTING TO THE RADIAL DRIVE BEVEL GEARSHAFT.  SIMILAR OCCURRENCE ON MID SPAN GEAR TRAIN SYSTEM ON OTHER ENGINES HAD CAUSE IN FLIGHT SHUTDOWN.                                                                                                                                                                                                                                                    2L72 4F4  FRTT00011ATTE6CH                
20060619002512006061900251EA  2006       6          19         CA060116003      220060106G8530AEL65102        CYLINDER                                PIPER PA30  PA30        7103002SO  LYC   O320  IO320B1A    41508EA  HARTZLHCE2Y HCE2YL2     GL  ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2192                                                           IN RESPONSE TO AD 2005-26-10 ISSUED BY THE FAA, INSPECTED AIRCRAFT TO DETERMINE IF ANY OF SUSPECT SN CYLINDERS INSTALLED.  FOUND 2 CYLINDERS ON LT ENGINE WERE PART OF THE AD REQUIREMENT FOR REPLACEMENT. ON CLOSER EXAMINATION OF ONE OF THESE CYLINDERS (NR 3), FOUND A CRACK EXTENDING FROM THE SPARK PLUG HOLE AROUND THE EXHAUST PORT AND PARTIALLY AROUND THE BARREL.  THERE WAS A SIGNIFICANT LEAK OF COMPRESSION.  BOTH CYLINDERS ARE PRESENTLY BEING REPLACED.  ALL OTHER CYLINDERS MADE BY ECI AND ON OUR AIRCRAFT WILL BE MONITORED CLOSELY AS REPLACE THEM ALL PER THE AD SCHEDULE.                                                                                                                                                1L72 3O3  O  A1EA    1E12    5  CP9EA     
20060619002532006061900253EU  2006       6          19         CA060116004      120060112G5347B530042         SEAT TRACK                              SAAB  SF340 340B        7860101EU                                                               BS 297-375      CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      DURING THE 4K2Y BRIDGE CHECK VISIT, THE AISLE LT SIDE SEAT TRACK BL 18.3 WAS FOUND TO HAVE AREAS OF CORROSION FORWARD OF FRAME STA 375 BEYOND ALLOWABLE LIMITS IAW SRM.  THE AISLE LT SIDE SEAT TRACK BL 18.3 WILL BE REPLACED WITH A NEW SEAT TRACK SECTION P/N B53004-2 AT FRAME STA 297-375 AND REPAIR BEAM P/N B53004-3 IAW THE COMPANY APPROPIATE EO.                                                                                                                                                                                                                                                                                                                                                                                      2L72 4T    RTA52EU                        
20060619002542006061900254EU  2006       6          19         CA060116005      120060103G2121TVT10728H3      COOLING FAN                             AMD   FALC90FALCON900B  2730171EU                                                                               SEIZED          W      H   DEACTIVATE SYST/CIRCUITS                                                                        B  SMOKE/FUMES/ODORS/SPARKS                                                      TXTAXI/GRND HDL  1                      CA       3067                                                           WHILE ON THE GROUND WITH THE APU RUNNING, SMOKE WAS OBSERVED IN THE CABIN.  THE CREW IMMEDIATELY SHUT DOWN THE APU.  THE TURBO COOLING FAN WAS FOUND SEIZED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L73 4F    RT                             
20060619000802006061900080EA  2006       6          19         CA060116006      220060111G852074968           CRANKSHAFT                              BBAVIA8     8GCBC       1220803SW  LYC   O360  O360C2E     41514EA  MCAULY1A200 1A200*      GL  ENGINE          CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            698                                                       THE CRANKSHAFT A/C WAS INSPECTED DUE TO A FAILURE OF A CRANKSHAFT ON ANOTHER AIRCRAFT IN THE FLEET (INTERNAL CORROSION).  UPON REMOVAL OF THE FRONT CRANK PLUG AND CLEANING OF THE CRANKSHAFT, IT DISCOVERED THAT URETHABOND COATING WAS BLISTERING.  URETHABOND REMOVED AND CORROSION WAS FOUND WITHIN FIRST INCH OF CRANK.  ENGINE WAS A FACTORY EXCHANGE OVERHAUL (21 APR 2002) AND THE CRANK HAD BEEN RE-WORKED.  THE CRANKSHAFT WAS AT MAX ID THEREFORE PITTING FROM CORROSION COULD NOT BE COMPLETLY REMOVED.  CRANK WAS INSPECTED BY AN APPROVED AMO(NDT) AS PER LYC SB 505B AND NO FAILING INDICATION WERE FOUND.  CRANK WAS MARKED PID AND DID NOT REQURIE ANY INTERNAL INSPECTIONS UNTIL 2000-HRS.                                    1H71 3O3  O  A21CE   E286    5  NP874     
20060619002552006061900255CE  2006       6          19         CA060116007      120060115G53400512128         BRACKET         CESSNA                  CESSNA185   A185F       2072821CE  CONT  O520  IO520D      17032SO  MCAULYD3A34 D3A34C401   GL  BS 65.33        BROKEN          W      L   ABORTED APPROACH                                                                                F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA       3815                                                           UPON APPROACH TO LAND ON LAKE, FLAPS 10 SELECTED.  A/C IMMEDIATELY BEGAN TO ROLL TO LT, RETURNED FLAPS TO ZERO, A/C RETURNED TO LVL FLT.  TRIED TO DEPLOY FLAPS AGAIN (SLOWLY) AND OBSERVED RT FLAP DEPLOYED NORMALLY,  LT FLAP DID NOT MOVE, A/C THEN RETURNED TO WHERE A FLAPLESS LANDING WAS CARRIED OUT WITH NO FURTHER PROBLEMS.  ONCE ON GROUND PILOT SELECTED FLAPS 10 AND NOTED WHILE RT FLAP DEPLOYED IMMEDIATELY, LT FLAP SLOWLY FELL TO POSITION.  ONCE IN HANGAR AND OPENED UP FOR INSPECT IT WAS DISCOVERED THAT FLAP PULLEY BRACKET (LT) AT STA 65.33 DETACHED/TORN FROM BULKHEAD ASSY THUS CAUSING PULLEY TO NO LONGER BE ATTACHED TO AIRFRAME CAUSING FLAP TO MALFUNCTION.  PILOT CONFIRMED FLAPS FUNCTIONING NORMALLY FOR T/O. 1H71 3O3  O  3A24    E5CE    5  CP47GL    
20060619002562006061900256SW  2006       6          19         CA060116008      120060113G5302205032814103    PANEL                                   BELL  412   412EP       1182205SW                                                               TAILBOOM        MISMANUFACTURED W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      MFG WAS ADVISED BY A SUPPLIER THAT PANELS WERE PROCESSED UNDER A DIFFERENT CURE CYCLE THAN THE ONE PRESCRIBED BY THE MFG PROCESS SPECIFICATION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1G72 4U      H4SW                         
20060619002572006061900257SW  2006       6          19         CA060116009      120060113G5302                PANEL                                   BELL  412   412EP       1182205SW                                                               TAILBOOM        MISMANUFACTURED W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      MFG WAS ADVISED BY A SUPPLIER THAT PANELS WERE PROCESSED UNDER A DIFFERENT CURE CYCLE THAN THE ONE PRESCRIBED BY THE MFG PROCESS SPECIFICATION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1G72 4U      H4SW                         
20060619002782006061900278NM  2006       6          19         CA060117001      120060117G7931                ENGINE                                  AIRBUSA319  A319114     3930350NM  GE    CFM56 CFM565A     13802NE                              NR 1            INOPERATIVE     W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            APAPPROACH       1                      CA                                                                      ECAM MSG ENG 1 LOW OIL PRESS ON APPROACH/AGAIN ON GRD DROPPED TO 13 PSI ENG SHUTDOWN.  TSM 79-00-00 PG 1, FOUND OVER 2 GAL OF OIL IN AGB-OIL DRAINED AND CKD SUPPLY FILTER/SCAVENGE FILTER AND MAG PLUGS.   ALL OK, CK AGB SCAVENGE LINE, CLEAR, CK OIL TANK STRAINER, CLEAR.  GRD RUN AT T/O POWER AND LEAK CK OK.                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F4  FRTA28NM   E29NE                
20060621000762006062100076NE  2006       6          21         CA060117002      220060117G7240                DUCT                                    CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30015NE                              14TH STG        FAILED          W      E   ENGINE SHUTDOWN                                                                                 F  FLT CONT AFFECTED                                                             DEDESCENT        1                      CA                                                                      L14TH DUCT MSG ON DESCENT.  ACTIONED CHECKLIST AND SHUTDOWN ENGINE.  CHANGED DETECTOR ELEMENT A59WK.  OP TEST CARRIED OUT IAW AMM SERV.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRTA21EA   E15NE                
20060621000772006062100077CE  2006       6          21         CA060117003      120060113G37107297088         GEAR                                    CESSNA172   172M        2072418CE  LYC   O320  O320E2D     41508EA  MCAULY1C160 1C160DTM    GL  VACUUM PUMP     SEIZED          W      ED  ENGINE SHUTDOWN         RETURN TO BLOCK                                                         O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA       858  858                                                       VACUUM PUMP DRIVE SHAFT SEIZED AND SHEARED OFF 2 GEAR TEETH.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H71 3O3  ONT3A12    E274    5  NP910     
20060621000792006062100079CE  2006       6          21         CA060117005      120060114G561010138402522     WINDSHIELD                              BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA                              COCKPIT         BROKEN          W      B   EMER. DESCENT                                                                                   O  OTHER                                                                         CRCRUISE         1                      CA                                                                      DURING CRUISE AT 19,000 FT ALTITUDE, CABIN DIFF OF 5.8 PSI, THE INNER PANE OF THE CO-PILOT'S WINDSHIELD SHATTERED.  THE CREW LANDED THE AIRCRAFT SAFELY AT IT'S DESTINATION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L72 4T4  T  A24CE   E4EA                 
20060621000812006062100081NM  2006       6          21         CA060118001      120060116G3040KCD4N           RELAY                                   DHAV  DHC8  DHC8*              NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF23      NE  COCKPIT         BURNED          W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      TXTAXI/GRND HDL  1                      CA                                                                      WHEN WINDSCREEN HEAT SELECTED TO WARM UP ON THE GROUND, SMOKE AND SPARKS CAME FROM RT FWD CORNER OF OVERHEAD PANEL. WINDSCREEN HEAT RELAY 3041-K6 FOUND BURNED, RELAY BASE ALSO FOUND DAMAGED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060621000822006062100082NE  2006       6          21         CA060118002      220060116G7200                ENGINE                                  BELL  212   212         1181420SW  PWA   PT6T  PT6T3B      52045NE                              NR 1            MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 YJ ENGINE STOPPAGE           WARNING INDICATION                                  DEDESCENT        1                      CA                                                                      (CAN) HELI-SKING: AC DROPPED SKIERS AT TOP, HAD LIFTED OFF MOUNTAIN TO GO TO SKIER PICK UP PAD.  AC WAS ON A DESCENDING, SLIDE SLIPPING,  PILOT CARRIED OUT A SCAN OF INDICATORS, NOTICE NR AT 99 PERCENT, DESCENDING TO 98 PERCENT, WAS EXPECTING A 101 PERCENT FOR HIM TO BEEP DWN TO 100 PERCENT. ENG OUT LIGHT NR1 ENG CAME ON AS WELL AS OTHER LIGHTS. NG, ITT WERE DECREASING ON NR 1 ENG. CREEPED NR BACK UP TO 100 PERCENT. ALSO CONFIRMED THAT THROTTLE WAS FULL OPEN. LEVEL OUT AC, ISOLATED DEAD PWR SEC AND RETURNED TO HANGAR. NORMAL SHUTDOWN ON NR 2 PWR SEC. MAINT BOTH PWR SEC WERE STARTED UP ON GROUND, BOTH PWR SEC STARTED NML, OPS CHECK APPEARED TO BE NML. AC GROUNDED TO TROUBLESHOOT THE DEFECT. (TC NR 20060118002)  1G71 4U4  U  H4SW    E22EA                
20060621000832006062100083NE  2006       6          21         CA060118003      220060117G74141050765         CLAMP           CONT        BL6006163   ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              MAGNETO COIL    FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            190   C019710E                                            ENGINE MAGNETO COIL CLAMP FAILED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1G71 3O3  O  H11NM   1E4                  
20060621001412006062100141NM  2006       6          21         CA060119003      120060117G323365C3575816      ACTUATOR                                BOEING727   727231      1384079NM  PWA   JT8   JT8D15A     52051NE                              UPLOCK          LEAKING         W      L   ABORTED APPROACH                                                                                J  WARNING INDICATION                                                            APAPPROACH       1                      CA                                                                      (CAN) ON APPROACH, NLG FAILED TO EXTEND NORMALLY. SUSPECT POSSIBLE FREEZING IN UPLOCK MECHANISM AND/OR BUNGEE LINK. MANUAL EXTENSION USED, NLG EXTENDED AND LOCKED. AIRCRAFT LANDED WITHOUT INCIDENT. UPON INSPECTION BY MAINTENANCE SUSPECTED ACTUATOR BYPASSING INTERNALLY. ACTUATOR REPLACED.  (TC NR 20060119003)                                                                                                                                                                                                                                                                                                                                                                                                                           2L73 4F4  F  A3WE    E2EA                 
20060621001432006062100143NM  2006       6          21         CA060119004      120060117G323369141001        ACTUATOR                                BOEING727   727231      1384079NM  PWA   JT8   JT8D15A     52051NE                              MLG             FROZEN          W      L   ABORTED APPROACH                                                                                J  WARNING INDICATION                                                            APAPPROACH       1                      CA                                                                      (CAN) ON APPROACH, NLG FAILED TO EXTEND NORMALLY. SUSPECT POSSIBLE FREEZING IN UPLOCK MECHANISM AND/OR BUNGEE LINK. MANUAL EXTENSION USED. NLG EXTENDED AND LOCKED. AIRCRAFT LANDED WITHOUT INCIDENT. UPON INSPECTION BY MAINTENANCE SUSPECTED BUNGEE ACTUATOR FROZEN. BUNGEE LINK REPLACED.  (TC NR 20060119004)                                                                                                                                                                                                                                                                                                                                                                                                                               2L73 4F4  F  A3WE    E2EA                 
20060621001452006062100145NM  2006       6          21         CA060119005      120060119G3297                WIRE HARNESS                            BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  NLG             DAMAGED         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA                                                                      (CAN) LANDING GEAR FAILED TO RETRACT: 3X RED AND 3X GREEN ON (UP) SELECTION. ON ARRIVAL THE ENGINEERS HAVE FOUND A FAULT WITH NWCENT UNREASONABLY FAR.  OPERATOR IS REPLACING THE WOW 2 HARNESS P/N 47151-5. (TC NR 20060119005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
20060621001472006062100147EA  2006       6          21         CA060120001      120060118G5610NP1393216       WINDSHIELD                              CNDAIRCL600 CL6002B19   1900309EA                                                               COCKPIT         CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA       27950                                                          (CAN) FO WINDSHIELD OUTER PLY CRACKED IN FLIGHT.  REMOVED AND REPLACED WINDSHIELD.   WINDSHIELD IS PRE AD 2001-35-R1 (BA SB 601R56-04). (TC NR 20060120001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F    RTA21EA                        
20060621001482006062100148SW  2006       6          21         CA060120002      120060117G6220206011111003    BEARING RACE                            BELL  206   206L1       1182107SW  ALLSN 250C  250C28B     03013GL                              M/R TRUNNION    CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) ON A SCHEDULED 1200 HR M/R CORROSION INSPECTION THE INNER RACE OF THE M/R TRUNNION BEARING WAS FOUND TO BE SEVERLY CORRODED TO THE POINT THAT THE INNER RACE WAS CRACKED. THIS BEARING RACE IS THERMALLY PRESS FIT AND THE TIGHT TOLLERANCE, SEVERE CORROSION AND FLIGHT LOADS CAUSED THIS RACE TO CRACK (TC NR 20060120002)                                                                                                                                                                                                                                                                                                                                                                                                              1G71 3U3  U  H2SW    E1GL                 
20060621001512006062100151NM  2006       6          21         CA060120003      120060119G291069744131        CONNECTOR       BOEING                  BOEING737   7378Q8      13844BXNM                                                               SHUTOFF VALVE   CRACKED         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       1815618156                                                     (CAN) RT ENGINE HYDRAULIC SHUTOFF VALVE FOUND LEAKING. FAULT TRACED TO CRACKED CONNECTOR - IPC REF 29-11-81-01, ITEM 50. CONNECTOR REPLACED. (TC NR 20060120003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F    RTA16WE                        
20060621001532006062100153EA  2006       6          21         CA060122001      120060119G33102LA0069137      LIGHT                                   CNDAIRCL600 CL6002C10   1390015EA                                                               COCKPIT         CONTAMINATED    W      A   UNSCHED LANDING                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA                                                                      (CAN) CO-PILOT'S FLOOD LIGHT BELOW I-STRAP AREA WAS CONTAMINATED BY WATER, WHICH SHORTED THE FLOOD LIGHT AND MELTED. (TC NR 20060122001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F    RTA21EA                        
20060621001542006062100154NM  2006       6          21         CA060123001      120060117G3233AE7128852       FLEX LINE                               BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R320  CR3204123F1 GL  NLG LOCK ACT    RUPTURED        W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       5895                                                           (CAN) CREW FOUND A PUDDLE OF THE HYDRAULIC FLUID ON THE GROUND AROUND OF THE NLG STRUT AFTER THE AIRCRAFT WAS PARKED. NLG WHEEL WELL WAS WET CONDITION. RESULT OF THE INSPECTION, FOUND WIRE BRAID BROKEN AND FLUID LEAKAGE ON THE FLEXIBLE HOSE CONNECTED TO THE NLG LOCK ACTUATOR (UP) SIDE. HYDRAULIC FLUID QTY OF THE NR 2 SYSTEM WAS DOWN TO 35 PERCENT.  THE BROKEN HOSE WAS REPLACED.  BOTH NOSE WHEEL ASSEMBLIES WERE REPLACED. NR 2 HYD FLUID LEVEL WAS ADJUSTED (REFILL).  LEAKAGE AND OPERATION CHECK NR 2 HYD SYSTEM (FLT CONTROL, STEERING)  OPERATION CHECK AND AIR BLEED NR 2 HYD SYSTEM WITH GHPU. (TC NR 20060123001)                                                                                                          2H72 4T4  TRTA13NM   E00062EN6  CP5NE     
20060621001552006062100155WP  2006       6          21         CA060123002      120060118G6730D2121           SERVO                                   ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              FLT CONTROLS    LEAKING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       621                                                            (CAN) SERVO REMOVED FROM SERVICE BECAUSE OF A HYDRAULIC FLUID LEAK.  SERVO WAS INSTALLED AT THE FACTORY. (TC NR 20060123002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1G71 3O3  O  H11NM   1E4                  
20060621001572006062100157GL  2006       6          21         CA060123003      220060121G72506898663         TURBINE WHEEL                           BELL  407   407         1182206SW  ALLSN 250C  250C47B          GL                              ENGINE          DAMAGED         W      BA  EMER. DESCENT           UNSCHED LANDING                                                         EJ VIBRATION/BUFFET          WARNING INDICATION                                  CRCRUISE         1                      CA       54                                                             (CAN) PILOT HEARD LOUD SQUEALING NOISE FOLLOWED BY VIBRATION WHILE IN CRUISE FLIGHT WITH PASSENGERS. ELECTED TO LAND IMMEDIATELY. NORMAL LANDING AWAY FROM BASE CARRIED OUT. INSPECTION FOUND DAMAGE TO ENGINE TURBINE SECTION, SUSPECT 3RD STAGE TURBINE WHEEL PROBLEM. ENGINE REMOVED AND REPLACED. TURBINE WILL BE SENT FOR INSPECTION. (TC NR 20060123003)                                                                                                                                                                                                                                                                                                                                                                                  1G71 3U3  UO H2SW    E1GL                 
20060623000312006062300031EA  2006       6          23         CA060123004      120060120G5630C3FS5152        WINDOW                                  DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A27      52043EA  HARTZLHCB3T HCB3TN3     GL  PAX DOOR        MISSING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) AFTER A TRAINING FLIGHT, AC CAME BACK TO DEPARTURE, WHERE ON THE VISUAL INSPECTION OF EXTERIOR OF FUSELAGE IT WAS NOTICED THAT RT AFT DOOR WAS MISSING EXTERIOR PART OF WINDOW (PLEXIGLASS) INCLUDING WEATHER STRIP AND THE FILLER STRIP. INTERIOR PART OF THE WINDOW (SCRATCH PANE) REMAINED IN PLACE. SURROUNDING AREA ON DOOR AND ALL AFT STRUCTURES THAT COULD HAVE BEEN IN CONTACT WITH THE WINDOWS TRAJECTORY WAS INSPECTED AND NO DAMMAGE WAS FOUND. AT THE TIME OF THIS REPORT, WINDOW, WEATHER AND FILLER STRIPS WERE ORDERED AND AWAITING PARTS.  OPERATOR HAS INITIATED A ONE-TIME FLEET INSPECTION ON COMPANY CAMPAIGN NOTICE 451-56-30-004. (TC NR 20060123004)                                                              1H72 3T4  TRTA9EA    E4EA    6  CP15EA    
20060623000462006062300046GL  2006       6          23         CA060123005      120060110G2560                INERTIA REEL                            DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO  SNSNCHW69EK W69EK63     EA  SHOULDER BELT   BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA       1725                                                           (CAN) PILOT REPORTED THAT THE REEL MECHANISM IN THE LT SHOULDER HARNESS ASSEMBLY ON THE RT SEAT WAS DEFECTIVE AND WAS NOT ALLOWING THE BELT TO RETRACT.  AFTER REMOVAL, THE BELT WAS FINALLY RETRACTED AFTER SHAKING THE LOOSE NYLON PIECES THAT HAD BROKEN, INSIDE THE REEL.  IT WAS THEN NOTED THAT THE BELT WOULD GO IN AND OUT AS IT NORMALLY DOES BUT THE INERTIA REEL WAS NO LONGER LOCKING. BELT ASSY. WAS REPLACED WITH NEW UNIT (TC NR 20060123005)                                                                                                                                                                                                                                                                                    1L71 3O3  ONTTA4CH   E7SO    5  NTA4CH    
20060623000472006062300047CE  2006       6          23         CA060123006      120060119G2897D3899926FJ4     PIN                                     LEAR  45    45LEAR      5170805CE  GARRTTTFE731TFE731*     01518WP                              CONNECTOR       BURNED          W      K   NONE                                                                                            B  SMOKE/FUMES/ODORS/SPARKS                                                      ININSP/MAINT     1                      CA       1996                                                           (CAN) WHILE DE-FUELING AC FOR ROUTINE MAINT, IT WAS DISCOVERED THAT LT WING WOULD NOT DE-FUEL. MAINT FOUND THAT STBY FUEL PUMP WAS NOT WORKING. TROUBLESHOOTING FOUND CONNECTOR PLUG P221 UNDER CENTER PEDESTAL HAD A BURNED PIN AND CONNECTOR.  PLUG AND CONNECTION BOTH SHOWED SIGNS OF OVERHEATING RESULTING FROM A SHORT CIRCUIT.  C/B PROTECTING THIS SYS NEVER TRIPPED.  IT IS A 15 AMP C/B.  INVESTIGATION REVEALED EICAS INDICATION FOR STBY PUMP WAS (ON), INDICATING PUMP WAS WORKING WHEN IT WAS NOT. CONNECTOR PLUG WAS REPLACED AND FUNCTION CHECKS CARRIED OUT, RETURNED TO SERVICE.  DISCUSSION WITH MFG FSR IS ON GOING TO DETERMINE HOW THIS COULD HAPPEN. (TC NR 20060123006)                                                 2L72 4F4  FRTT00008WIE6WE                 
20060623000492006062300049CE  2006       6          23         CA060124001      120060121G32331158100283      PINION GEAR     BEECH                   BEECH 99    99          1154002CE  PWA   PT6   PT6A28           EA  HARTZLHCB3T HCB3TN3     GL  ACTUATOR        BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            937   ALG5856                                             (CAN) THE GEAR ACTUATOR WAS REMOVED FROM THE AIRCRAFT FOR A RELUBE AND END PLAY CHECK IAW AD72-10-04R2 PART B AND C.  WHEN IT WAS CLEANED UP THE MECHANIC NOTICED THAT SEVERAL OF THE TEETH ON THE PINION GEAR WERE BROKEN OFF.  THERE WAS NO OBVIOUS REASON FOR FAILURE OF THE TEETH.  THIS WAS THE FIRST INSPECITON SINCE THE ACTUATOR WAS INSTALLED AFTER OVERHAUL.  THE ACTUATOR ALSO FAILED THE END PLAY CHECK BY .003 THOUSANDS OF AN INCH. (TC NR 20060124001)                                                                                                                                                                                                                                                                           1L72 3T4  T  A14CE   E4EA    6  CP15EA    
20060705000212006070500021SW  2006       7          5          CA060124002      120060120G2720315372LR        RUDDER PEDAL                            BBAVIA8     8GCBC       1220803SW  LYC   O360  O360C2E     41514EA  MCAULY1A200 1A200*      GL  COCKPIT         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       7559                                                           (CAN) DURING THE COMPANY STRUCTURAL INSPECTION AND REPAIR PROGRAM (SIRP), THE AIRCRAFT RUDDER PEDALS WERE SENT FOR NDT INSPECTION WHERE IT WAS DISCOVERED THAT BOTH LT AND RT REAR RUDDER PEDALS WERE CRACKED.  THESE PEDALS ARE AN OLDER STYLE PEDAL AND ARE NO LONGER AVAILABLE FROM MFG.  (TC NR 20060124002)                                                                                                                                                                                                                                                                                                                                                                                                                                1H71 3O3  O  A21CE   E286    5  NP874     
20060623000562006062300056EU  2006       6          23         CA060124003      120060119G6710ASNA00190961    SPHERICAL STOP                          UROCOPEC120 EC120B      8680987EU  TMECA ARRIUSARRIU2F          NE                              COLLECTIVE      CORRODED        W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             CRCRUISE         1                      CA       3341                                                           (CAN) ON MONDAY 16 JANUARY 2006, PILOT REPORTED COLLECTIVE WAS ROUGH AT HIGH POWER SETTING. HE WAS UNABLE TO REPLICATE. (TC NR 20060124003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1G72 3U3  UNCR0001RD E34NE                
20060623000612006062300061SO  2006       6          23         CA060124004      120060124G27206342008         BELLCRANK                               PIPER PA28  PA28140     7102802SO  LYC   O320  O320E3D     41508EA  SNSNCH74D   74DM        EA  RUDDER CABLE    CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1725017250                                                     (CAN) CRACKS ON THE LT RUDDER CABLE ATTACHING BELLCRANK FOR MORE INFORMATION INCLUDING PICTURES CONTACT SUBMITTER. (TC NR 20060124004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L71 3O3  O  2A13    E274    5  NP88614   
20060623000622006062300062NM  2006       6          23         CA060124005      120060118G7160                ARM             ROTAX                   AMBLP A150  A150        3850110NM  ROTAX 912   ROTAX912F3       EU                              AIRBOX          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1490                                                           (CAN) ENGINE RECIEVED FOR OVERHAUL WITH AIRBOX INSTALLED. THE CARB DRIP TRAYS ARE CONNECTED TO THE AIRBOX BY A SUPPORT ARM WITH TWO SCREWS HOLDING THE TRAYS ONTO THE SUPPORT ARM. THE DRIP TRAY SUPPORT ARM WAS FOUND CRACKED AT THE HOLES FOR THE SCREWS. (TC  20060124005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1B72 3O3  O0 SOOOO2SEE00051EN             
20060623000632006062300063NE  2006       6          23         CA060124006      220060118G73218063489         FUEL CONTROL                            CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30015NE                              NR 1 ENGINE     UNSERVICEABLE   W      E   ENGINE SHUTDOWN                                                                                 O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA       178723225                          807342                      (CAN) NR 1 ENGINE FAILED TO START WITH IGNITION OPERATING NORMALLY.   5 ATTEMPTS WERE MADE BY THE FLIGHT CREW.  GROUND PERSONNEL NOTED EXTREME AMOUNT OF FLAMES COMING FROM THE JETPIPE AND ADVISED FLIGHT CREW.  FUEL CONTROL SN WYG85082 REPLACED, ENGINE GROUND RUN, STARTS NORMAL. GROUND CHECKED SERVICEABLE.  FDR DOWNLOAD SHOWED 2300 LBS OF FUEL FLOW ON START. NORMAL FUEL FLOW ON START EQUALS APPROX. 400 LBS. AFFECTED MFC IS BEING SENT FOR INVESTIGATION AND CORRECTIVE ACTION AS APPLICABLE.  (TC NR 20060124006)                                                                                                                                                                                                                2L72 4F4  FRTA21EA   E15NE                
20060623000642006062300064NM  2006       6          23         CA060125001      120060119G3297471515          WIRE HARNESS                            BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  NLG             INOPERATIVE     W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA       2764                                                           (CAN) AFTER TAKEOFF AND LANDING GEAR SELECTED UP, ALL GREEN AND RED UNLOCK LIGHTS REMAINED ON. AIRCRAFT RETURNED TO AIRPORT.    MAINT: PSEU PRESENT FAULTS NG WOW 2, NWCENT LOGGED. LANDING GEAR RETRACTION TEST CONFIRMED FAULT. HARNESS RESISTANCE CHECK CONFIRMED OPEN CIRCUIT. REPLACED WOW2/NWCENT HARNESS ASSY THEN LDG AND NW STEERING TESTED OK. (TC NR 20060125001)                                                                                                                                                                                                                                                                                                                                                                    2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
20060623000652006062300065CE  2006       6          23         CA060125002      120060120G311007601316        COLLAR                                  CESSNA172   172N        2072434CE  LYC   O360  O360A4A     41514EA  SNSNCH76E   76EM8S5     EA  INSTRUMENT PANELCRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1299                                                           (CAN) DURING INSPECTION THE PILOT CONTROL COLUMN WAS NOTICED TO HAVE MORE MOVEMENT OFF-AXIS THAN THE CO-PILOT CONTROL PANEL.  THE PILOT'S CONTROL COLUMN SUPPORT & LOCK COLLAR WAS FOUND TO BE CRACKED LONGITUDINALLY AND WAS REPLACED NEW. (TC# 20060125002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3O3  ONT3A12    E286    5  NP4EA     
20060623000672006062300067CE  2006       6          23         CA060125003      120060119G27102660001114      CONTROL CABLE                           CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE  MCAULY3AF34C3GFR34C703  GL  AILERONS        DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING NORMAL INSPECTION IT WAS FOUND THAT ONE OF THE AILERON WING LOOP CABLES WAS WEARING INTO THE SIDE OF THE LIGHTNING HOLE OF THE FIRST WING RIB ON THE LT WING.  THE CABLE WAS DAMAGED AS WELL.  THE AIRCRAFT WAS GROUNDED UNTIL THE CABLE WAS REPLACED, THE DAMAGE TO THE LIGHTNING HOLE WAS DRESSED OUT AND THE RUBBER SEAL/GUIDE JUST IB OF THE WING RIB (ON THE FUSELAGE) WAS REPLACED.  THE OTHER CARAVANS IN OUR FLEET WERE INSPECTED IN THAT AREA, NO OTHER DEFECTS WERE FOUND. (TC NR 20060125003)                                                                                                                                                                                                                           1H71 3T3  T  A37CE   E4EA    5  CP60GL    
20060626001292006062600129CE  2006       6          26         CA060125004      120060124G535050910276BSC     CAM                                     BEECH 1900  1900C       1154161CE  PWA   PT6   PT6A65B     52043EA  HARTZLHCB4M HCB4MP3     GL                  BROKEN          W      O   OTHER                                                                                           O  OTHER                                                                         APAPPROACH       1                      CA       2298022980                                                     HEARD A BANG DURING APPROACH, FOUND RT UPPER FWD COWL INNER PORTION HAD LIFTED FROM NORM POSITION.  FOUND CAM BOLT FAILED THAT PROVIDES TENSION TO LWR COWL ASSY.  OVER CTR COWL FASTENERS ON THESE A/C (4) INSTILL CONSIDERABLE FORCE AND HAVE A HISTORY ON ALL SIMILAR INSTALLATIONS WITH VARIOUS FAILURE MODES.  AS A RESULT, INSTALLED A BACKUP SYS OF PROVIDING HARDPOINTS TO ALLOW .032 LOCKWIRE TO BE INSTALLED BETWEEN TWO COWL HALVES, SHOULD ANY OF CAM POINTS FAIL.  LOCKWIRE ON INBD POINTS ALSO FAILED BUT OUTER POINTS HELD THRU CONCLUSION OF FLT.  COWL SUSTAINED SOME DAMAGE REQUIRING REPLACEMENT.  NOW LOOKING AT DEVELOPING AN STC TO REMOVE ORIG CAM SYS ENTIRELY AND GOING WITH AN OVERLAP ARRANGEMENT AND SEVERAL CAMLOCK2L72 4T4  TRTA24CE   E4EA    6  CP56GL    
20060623001362006062300136EA  2006       6          23         CA060125005      220060119G741410382585        POINTS          BENDIX                  PIPER PA44  PA44180     7104402SO  LYC   O360  O360E1A6    41514EA  HARTZLHCC2Y HCC2YR2     GL  MAGNETO         WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       160                                                            (CAN) WHEN PERFORMING GROUND RUNUP,CHECKING MAGS ON RT ENG,  ENG WOULD QUIT WHEN RUNNING ON LT MAG ONLY.  TROUBLESHOOTING REVEAL THAT LT POINTS WERE WORN SO MUCH THAT THEY WERE NOT OPENNING.  POINTS WERE REPLACED AND ENGINE RAN NORMAL AGAIN. THIS HAS BEEN RECURRING, INTERMITTENT PROBLEM, WHERE YOU CANNOT COUNT ON HOW LONG THE POINTS WILL LAST.  PLASTIC NYLON ARM THAT RIDES ON THE CAM, WEARS PREMATURELY UNTIL ITS WORN SO MUCH THAT THE POINTS NO LONGER OPEN AND THEN IT QUITS FIRING.  SAME PROBLEM WITH THE DUAL MAGNETO.   ALSO IT IS A DIFFICULT AREA TO GET AT TO SEE THE PONTS, USUALLY IT'S ON A 500 HOUR INSPECTION ITEM.  (TC NR 20060125005)                                                                           1L72 3O3  O  A19S0   E286    5  CP920     
20060623001732006062300173EA  2006       6          23         CA060125006      220060113G7322                SHAFT SEAL                              BEECH 90    C90A        1152911CE  PWA   PT6   PT6A21      52043EA  HARTZLHCB3T HCB3TN3     GL  FUEL PUMP       LEAKING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            4185  A75755                                              (CAN) WHILE DOING A GROUND RUN TO VERIFY THE COMPASS SYSTEM, TECH NOTICED UNCOMMANDED ACCELERATION AND DECELERATION OF THE RT ENGINE.  VISUAL INSPECTION IDENTIFIED BLUE DYE WASHOUT FROM THE FUEL PUMP TO FUEL CONTROL UNIT SEAL AREA AND CONFIRMED A FAULT. THE FUEL CONTROL UNIT AND FUEL PUMP ASSEMBLY WERE REMOVED AND REPLACED WITH SERVICEABLE UNITS.   (TC NR 20060125006)                                                                                                                                                                                                                                                                                                                                                              1L72 3T4  TRT3A20    E4EA    6  CP15EA    
20060623001762006062300176    2006       6          23         CA060125007      420060125G3100                UNKNOWN                                 EMB   ERJ190ERJ190100IGW3260408EU  GE    CF34  CF34*            NE                              UNKNOWN         MULTIPLE FAIL   W      D   RETURN TO BLOCK                                                                                 G  MULTIPLE FAILURE                                                              TXTAXI/GRND HDL  1                      CA                                                                      (CAN) ON TAXI OUT (TWICE) EICAS MESSAGES A/T FAIL, A/P FAIL, AFCS FAIL, MACH TRIM FAIL, SHAKER, ANTICIPATED, ADS 2 FAIL, TAT NR 2 FAIL,ADS FAIL, WINDSHEAR FAIL, AOA LIMIT FAIL, ADS PROBE NR 1 FAIL, ADS PROBE NR 2 FAIL, ADS PROBE NR 3 FAIL, ADS PROBE NR 4 FAIL, STALL PROTECTION FAIL, YD FAIL, ECT.  ACTION: ADS PROBES, ADS SYSTEM, TEST CARRIED OUT IAW AMM 34-13-01-06 SYSTEM CHECKS SERVICEABLE. STILL UNDER INVESTIGATION WITH FLEET MANAGEMENT AND MFG ENGINEERING.  (TC NR 20060125007)                                                                                                                                                                                                                                            2L72 4F4  FRTA57NM   E15NE                
20060623001772006062300177SO  2006       6          23         CA060125008      120060124G55406342008         BAR                                     PIPER PA28  PA28140     7102802SO  LYC   O320  O320E3D     41508EA  SNSNCH74D   74DM        EA  RUDDER          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1724917249                                                     (CAN) PILOTS SIDE LT RUDDER BAR, CRACK FOUND ON COLLER BETWEEN ACCUATING ARM (FOR RUDDER CABLE) AND RUDDER BAR.  2 ADDITIONAL CRACKS WERE FOUND ADJACENT TO THE INITAL CRACK. (TC NR 20060125008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L71 3O3  O  2A13    E274    5  NP88614   
20060623001782006062300178CE  2006       6          23         CA060126001      120060125G5520115610010325    TORQUE TUBE     BEECH       115610010341BEECH 99    99          1154002CE  PWA   PT6   PT6A28           EA  HARTZLHCB3T HCB3TN3     GL  ELEVATOR        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            1850                                                      (CAN) DURING THE 100 HR INSPECTION THE TAIL CONE WAS REMOVED TO INSPECT THE TORQUE TUBES IAW INSPECTION PACKAGE.  THE LT TORQUE TUBE WAS FOUND CRACKED AROUND HALF THE TUBE BRACE.  IT HAD BEEN 100 HRS SINCE THE LAST INSPECTION. THE PN OF THE BRACKET IS 115-610018-1 (TC NR 20060126001)                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L72 3T4  T  A14CE   E4EA    6  CP15EA    
20060724000892006072400089NE  2006       7          24         CA060126002      220060118G7200CT78A           ENGINE                                                                     GE    CT7TP CT7TP*      30030NE                              NR 2            MAKING METAL    W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA       686                                                            NR 2 ENGINE CHIP LIGHT WAS EXPERIENCED ON OB LEG TO THE FPSO.  THE AIRCRAFT WAS TURNED AROUND FOR DEPARTURE POINT.  THERE WAS A SECOND INDICATION OF OIL BYPASS, HIGHER TGT AND LOWER OIL PRESSURE.  ENGINE WAS SHUTDOWN BY THE FLIGHT CREW.  THE AIRCRAFT RETURNED TO BASE ON SINGLE ENGINE WITHOUT FURTHER INCIDENT.  UPON ARRIVAL BACK TO BASE THE ENGINE WAS INVESTIGATED AND FOUND TO HAVE METAL CONTAMINATION ON THE CHIP PLUG AND SUMP SCREENS.  THE ENG WAS REPLACED AND FORWARDED TO THE MFG FOR A FURTHER INVESTIGATION.                                                                                                                                                                                                                     4  T          E8NE                 
20060623001802006062300180    2006       6          23         CA060126005      420060123G233050401100003     VIDEO DISPLAY                           BOEING737   737*               NM  CFMINTCFM567CFM567B22   13802NE                              SEAT 11B        SMOKE           W      H   DEACTIVATE SYST/CIRCUITS                                                                        B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA                                                                      (CAN) ON JANUARY 23, 2006 A/C WAS IN CRUISE WHEN SMOKE WAS OBSERVED COMING FROM SEAT 11B VDU. THE IFE SYSTEM WAS DEACTIVATED. MAINTENANCE REPLACED THE VDU AND THE SYSTEM WAS TESTED SERVICEABLE. THIS COMPONENT WILL BE RETURNED TO THE MANUFACTURER AND A COMPLETE TEARDOWN REPORT WILL BE REQUESTED. THIS SDR WILL BE UPDATED ONCE THAT INFORMATION IS AVAILABLE. (TC NR 20060126005)                                                                                                                                                                                                                                                                                                                                                        2L72 4F4  FRTA16WE   E00055EN             
20060623001812006062300181WP  2006       6          23         CA060126006      120060126G53435484911503      ATTACH FITTING  DOUG                    DOUG  DC6   DC6A        3021706WP  PWA   R1340 CWASP       52016NE  HAMSTD43E   43E60       NE  MLG             CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       42266                                                          (CAN) DURING ANNUAL INSPECTION, AD 89-11-07 WAS BEING ACCOMPLISHED. THE LT IB MLG ATTACH FITTING WAS FOUND TO BE CRACKED BETWEEN THE 4TH AND 5TH FASTENER HOLES ON THE OB VERTICAL LEG. THERE WERE 2 CRACKS NOTED. THE LENGTH OF THE CRACK RUNNING BETWEEN THE 2 FASTENER HOLES IS APPROXIMATELY .7500 INCH.  THERE WAS A SECOND CRACK NOTED RUNNING IN AN OUTWARD DIRECTION AND IS APPROXIMATELY .2500 INCH IN LENGTH. THE FITTING IS BEING REPLACED WITH A SERVICEABLE FITTING. (TC NR 20060126006)                                                                                                                                                                                                                                           2L74 4R3  R  6A3     ATC14   6  CP871     
20060623001832006062300183GL  2006       6          23         CA060126007      320060120G6111T10282N         BLADE           HARTZL      HCB3TN5     SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP  HARTZLHCB3T HCB3TN5     GL  PROPELLER       DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            2390  BVA7387                             BVA7387         (CAN) DISCOVERED WARPED TRAILING EDGE OF PROPELLER BY MAINTENANCE.  UNIT HAD BEEN OVERHAULED FEB 2003 THEN RETURNED FOR THIN TRAILING EDGE APRIL 2003.  REPAIRED BY SAME FACILITY.  TRAILING EDGE WAS SIGNIFICANTLY THINNER THAN SIMILAR IN FLEET.  REMOVED PROPELLER FROM SERVICE. (TC NR 20060126007)                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4T4  TRTA8SW    E4WE    6  CP15EA    
20060623001842006062300184CE  2006       6          23         CA060126008      120060124G5540MS289135        BEARING         BEECH       1306300001  BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE  HARTZLHCE4A HCE4A3I     NE  RUDDER          WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                  207                                                 (CAN) DURING A GENERAL WALKAROUND THE RUDDER WAS MOVED BY HAND. NOTICING THAT THE RUDDER SEEMED TO MOVE UP AND DOWN AND APPEARED TO RUB AGAINST THE TAIL CONE. RUDDER ATTATCHMENT INSPECTED. INVESTIGATION REVEALED THAT ALL THREE BEARINGS HAVING SOME PLAY. THE LOWER BEARING SEEMED TO CAUSE THE RUDDER TO DROP. THIS INTURN WORE THE CLEVIS BRACKETS. REPLACED ALL THREE BEARINGS AND BOTH CLEVIS BRACKETS. RUDDER REINSTALLED AND TRAVEL CHECKED OK. AIRCRAFT RETURNED TO SERVICE. (TC NR 20060126008)                                                                                                                                                                                                                                     2L72 4T4  TRTA24CE   E26NE   5  CP10NE    
20060623001872006062300187NM  2006       6          23         CA060127001      120060127G541085410617005     DOOR                                    DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF23      NE  RT NACELLE      SEPARATED       W      O   OTHER                                                                                           D  INFLIGHT SEPARATION                                                           TXTAXI/GRND HDL  1                      CA                                                                      (CAN) ON ARRIVAL TO BASE, THE DOOR FOR THE REFUEL PANEL WAS FOUND TO HAVE SEPARATED FROM THE NACELLE. THE HINGES, HINGE ATTACHMENT BOLTS AND SMALL FRAGMENTS OF THE COMPOSITE PANEL REMAINED ATTACHED. (TC NR 20060127001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060623002032006062300203    2006       6          23         CA060127002      420060123G2562ELT10           ELT                                     BEECH 100   A100        1152915CE  PWA   PT6   PT6A28           EA  HARTZLHCD4N3HCD4N3A     GL  CABIN           INTERMITTENT    W      K   NONE                                                                                            L  NO TEST                                                                       ININSP/MAINT     1                      CA            50                                                        (CAN) ELT FAILED THE ACTIVATION TEST DURING THE ROUTINE INSPECTION.  THE UNIT HAD THE BATTERY REPLACED AND RECERTIFIED 21 DAYS EARLIER.  AVIONICS SHOP FOUND THE PROBLEM TO BE A INTERMITTENT ON/OFF SWITCH. (TC NR 20060127002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L72 3T4  T  A14CE   E4EA    5  CSTC      
20060623002042006062300204CE  2006       6          23         CA060127003      120060119G7333903800097       INDICATOR                               BEECH 90    F90         1152909CE  PWA   PT6   PT6A135     52043NE  HARTZLHCB4T HCB4TN3     GL  FUEL FLOW       FAILED          W      O   OTHER                                                                                           N  FALSE WARNING                                                                 CRCRUISE         1                      CA                                                                      (CAN) FUEL FLOW INDICATIONS WENT INTERMITTENT THEN FAILED IN FLIGHT.  FOUND TRANSMITTER TO HAVE FAILED INTERNALLY.  TIME ON UNIT APROX.5000 HRS. (TC NR 20060127003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L72 4T4  T  A31CE   E4EA    6  CP40EA    
20060623002052006062300205CE  2006       6          23         CA060127004      120060126G510010038900161     SWITCH                                  BEECH 100   A100        1152915CE  PWA   PT6   PT6A28           EA  HARTZLHCD4N3HCD4N3A     GL  FUEL DRAIN      UNSERVICEABLE   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) FLOAT SWITCH FAILED INTERNALLY CAUSING THE EPA CAN TO DRAIN OVERBOARD ON SHUTDOWN. (TC NR 20060127004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L72 3T4  T  A14CE   E4EA    5  CSTC      
20060623002062006062300206EU  2006       6          23         CA060127005      220060124G7260DART5342        ENGINE                                  BRAERO748   HS7482A     4231001EU  RROYCEDART  DART5342         EU  ROTOL R4304 R2124304    EU  NR 1            FAILED          W      H   DEACTIVATE SYST/CIRCUITS                                                                        YJ ENGINE STOPPAGE           WARNING INDICATION                                  DEDESCENT        1                      CA                                                                      (CAN) ON DESCENT INTO AIRPORT, THE NR 1 ENGINE FAILED. THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. (TC NR 20060127005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 3T4  T  A24EU   A196    6  CP899     
20060711001162006071100116SW  2006       7          11         CA060127006      120060127G321071461           LANDING GEAR                            BBAVIA8     8GCBC       1220803SW  LYC   O360  O360C2E     41514EA  MCAULY1A200 1A200*      GL                  CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       796                                                            (CAN) 2 SMALL CRACKS UNDER UPPER RADIUS OF LANDING GEAR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1H71 3O3  O  A21CE   E286    5  NP874     
20060623002082006062300208EU  2006       6          23         CA060127007      120060127G3097330A63622309    WIRE HARNESS                            SNIAS AS332 AS332L      8680809EU  TMECA MAKILAMAKILA1A    60040EU                              DE ICE SYS      WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       101                                                            (CAN) A/C RETURNED FROM AN OFFSHORE TRIP, THE MAINTENANCE STAFF WERE CARRING OUT A ROUTINE TURN AROUND CHECK AND FOUND THE M/R DEICE HARNESS BROKEN AT THE CONNECTOR PLUG. MAINTENANCE DEPT REPLACED THE HARNESS AND THE A/C RETURNED TO THE FLYING SCHEDULE. (TC NR 20060127007)                                                                                                                                                                                                                                                                                                                                                                                                                                                               2G72 4U4  U  H4EU    E12NE                
20060623002102006062300210NE  2006       6          23         CA060129001      220060125G7261PW535A          ENGINE                                  CESSNA500   560CESSNA   2076750CE  PWA   530   PW535A           NE                                              LOW PRESSURE    W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE, THE LOW OIL PRESSURE WARNING ANNUNCIATED.  THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED FOR AN UNSCHEDULED LANDING. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060129001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F4  FRTA22CE   E00053EN             
20060623002122006062300212NE  2006       6          23         CA060129002      220060115G732250099820        PUMP                                    AEROSPATR72 ATR72              EU  PWA   PW120 PW127            NE                              FUEL BOOST      FAULTY          W      E   ENGINE SHUTDOWN                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE, THE ENGINE LOST POWER AND WAS SHUTDOWN INFLIGHT.  SUBSEQUENT INVESTIGATION DETERMINED THE HYDROMECHANICAL FUEL CONTROL TO BE FAULTY.  FUEL CONTROL AND FUEL PUMP WERE REPLACED. (TC NR 20060129002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2H72 4T4  TRT        E20NE                
20060626000652006062600065NE  2006       6          26         CA060129004      220060123G7200PW545A          ENGINE                                  CESSNA500   560CESSNA   2076750CE  PWA   545   PW545A           NE                                              DAMAGED         W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         KAJFLUID LOSS                FLAME/FIRE                WARNING INDICATION        CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB, THE CREW OBSERVED ENGINE TEMPERATURE AND FUEL FLOW SPLIT. THE FLIGHT DIVERTED TO POINT OF DEPARTURE AND THE ENGINE WAS SHUT DOWN DURING DESCENT.  SUBSEQUENT INSPECTION REVEALED DAMAGE TO THE ENGINE INNER BYPASS DUCTING CONSISTENT WITH AN INTERNAL ENGINE FIRE.  MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060129004)                                                                                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA22CE   E00059EN             
20060626000762006062600076EA  2006       6          26         CA060129005      220060120G7200                ENGINE                                  BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA                                              FIRE            W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         ARJFLAME/FIRE                PARTIAL RPM/PWR LOSS      WARNING INDICATION        CLCLIMB          1                      CA                                                                      (CAN) THE ENGINE WAS REPORTED TO EMIT A LOUD NOISE ACCOMPANIED BY A LOSS IN POWER AND FLAMES EMINATING FROM THE EXHAUST.  THE ENGINE WAS SHUT DOWN IN FLIGHT.  MFG WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20060129005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1L72 4T4  T  A24CE   E4EA                 
20060626000772006062600077NE  2006       6          26         CA060129006      220060118G7200                ENGINE                                  CESSNA500   560CESSNA   2076750CE  PWA   530   PW535A           NE                                              FLAMED OUT      W      O   OTHER                                                                                           XJ ENGINE FLAMEOUT           WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA                                          DC0262                      (CAN) THE ENGINE FLAMED OUT DURING GROUND HANDLING OPERATIONS.  MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060129006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F4  FRTA22CE   E00053EN             
20060626000782006062600078    2006       6          26         CA060129007      420060112G61223037685         GOVERNOR                                PILATSPC12  PC12        7090550EU  PWA   PT6   PT6A67B     52043NE                              OVERSPEED       FAULTY          W      A   UNSCHED LANDING                                                                                 RF PARTIAL RPM/PWR LOSS      FLT CONT AFFECTED                                   CRCRUISE         1                      CA       1599 1                                                         (CAN) DURING CRUISE THE PROPELLER SPEED DECREASED. AN UNSCHEDULED LANDING WAS CARRIED OUT WHICH RESULTED IN A PROPELLER STRIKE.  SUBSEQUENT INSPECTION REVEALED A FAULTY PROPELLER OVERSPEED GOVERNOR.  IAW WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20060129007)                                                                                                                                                                                                                                                                                                                                                                                                                                            1L71 3T4  TRTA78EU   E26NE                
20060626000792006062600079NE  2006       6          26         CA060129008      220060110G7321                FUEL CONTROL                            BELL  412   412         1182202SW  PWA   PT6T  PT6T3B      52045NE                              ENGINE          FAULTY          W      A   UNSCHED LANDING                                                                                 RXJPARTIAL RPM/PWR LOSS      ENGINE FLAMEOUT           WARNING INDICATION        CRCRUISE         1                      CA                                                                      (CAN) DURING FLIGHT, THE ENGINE LOST POWER FOLLOWED BY (ENGINE OUT) AND (LOW ROTOR SPEED) WARNING ANNUNCIATIONS. A SINGLE-ENGINE UNSCHEDULED LANDING WAS CARRIED OUT.  SUBESQUENT INSPECTION REVEALLED A FAULTY AUTOMATIC FUEL CONTROL UNIT.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20060129008)                                                                                                                                                                                                                                                                                                                                                                                                      1G72 4U4  U  H4SW    E22EA                
20060626000812006062600081NE  2006       6          26         CA060129010      220060111G7200                ENGINE                                  PILATSPC12  PC12        7090550EU  PWA   PT6   PT6A67B     52043NE                                              MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         NRNOT REPORTED   1                      CA                                          PR0565                      (CAN) DURING FLIGHT TEST OPERATIONS (PERFORMING ENGINE RELIGHT) ENGINE DID NOT RELIGHT.  A DEADSTICK LANDING WAS ACCOMPLISHED.  MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060129010)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L71 3T4  TRTA78EU   E26NE                
20060626000822006062600082NE  2006       6          26         CA060129011      220060111G7200                ENGINE                                  PROPJT200   200A        0140304NM  PWA   306   PW306B           NE                                              SHUTDOWN        W      O   OTHER                                                                                           YJ ENGINE STOPPAGE           WARNING INDICATION                                  LDLANDING        1                      CA                  CC0045                                              (CAN) ON ROLL OUT FOLLOWING LANDING, THE PILOT REPORTED AN UNCOMMANDED ENGINE SHUT DOWN.  THE ENGINE BLEED VALVES AND BLEED VALVE SOLENOID WERE SUBSEQUENTLY REPLACED. (TC NR 20060129011)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L71 3O4  F  3A18    E35NE                
20060626000832006062600083CE  2006       6          26         CA060129012      120060102G7931PT6A6D          ENGINE                                  BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE                                              LOW PRESSURE    W      C   ABORTED TAKEOFF                                                                                 J  WARNING INDICATION                                                            TOTAKEOFF        1                      CA                                                                      (CAN) DURING TAKE-OFF ROLL, THE ENGINE LOW PRESSURE WARNING ANNUNCIATED AND THE TAKE-OFF WAS ABORTED.  MFG WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060129012)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4T4  TRTA24CE   E26NE                
20060626000842006062600084EA  2006       6          26         CA060129013      220060102G7230                COMPRESSOR                              BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA  HARTZLHCD4N3HCD4N3A     GL  ENGINE          DAMAGED         W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  DEDESCENT        1                      CA                                          81119                       (CAN) DURING DESCENT, THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION, ACCOMPANIED BY NOISE AND FLAMES EMANATING FROM THE EXHAUST.  THE ENGINE WAS SHUT DOWN IN FLIGHT, AN EMERGENCY DECLARED AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED COMPRESSOR SECTION DAMAGE.  MFG WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060129013)                                                                                                                                                                                                                                                                                                                1L72 4T4  T  A24CE   E4EA    5  CSTC      
20060626000862006062600086NM  2006       6          26         CA060129014      120060104G7900                ENGINE                      PW308C      AMD   FALC50FALCON2000  2730170NM  PWA   306   PW306B           NE                                              ODOR            W      O   OTHER                                                                                           BOOSMOKE/FUMES/ODORS/SPARKS  OTHER                     OTHER                     NRNOT REPORTED   1                      CA                                          CF0049                      (CAN) THE ENGINE WAS REPORTED TO EXHIBIT OIL SMELL IN CABIN AIR ACCOMPANIED BY HIGH OIL CONSUMPTION.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20060129014)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2K72 4F4  FRTA50NM   E35NE                
20060626000882006062600088EU  2006       6          26         CA060129015      120060103G361031B576201       LINE                                    BRAERO1000  BAE1251000  1500287EU  PWA   305   PW305B      52128NE                              PNEUMATIC SYS   FRACTURED       W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         N  FALSE WARNING                                                                 CLCLIMB          1                      CA                                                                      (CAN) FOLLOWING TAKEOFF, THE ENGINE FIRE WARNING ANNUNCIATED AND THE ENGINE WAS REPORTED TO BE (TRAILING SMOKE).  THE ENGINE WAS SHUTDOWN IN FLIGHT, AN EMERGENCY DECLARED AND THE FLIGHT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED NO EVIDENSE OF FLUID LOSS OR FIRE. A BLEED VALVE PNEUMATIC TUBE WAS FOUND FRACTURED. (TC NR 20060129015)                                                                                                                                                                                                                                                                                                                                                                              2L72 4F4  FRTA3EU    E35NE                
20060703000502006070300050NE  2006       7          3          CA060129019      220060102G7200                ENGINE                                  LEAR  60    60LEAR      5170707CE  PWA   305   PW305A      52128NE                                              MALFUNCTIONED   W      E   ENGINE SHUTDOWN                                                                                 JA WARNING INDICATION        FLAME/FIRE                                          TXTAXI/GRND HDL  1                      CA                                                                      DURING START, AN ENGINE FADEC WARNING LIGHT ANNUNCIATED ACCOMPANIED BY FUEL AND FLAME EMANATING FROM THE ENGINE EXHAUST.  THE START WAS ABORTED.  PWC WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F4  FRTA10CE   E35NE                
20060703000512006070300051NE  2006       7          3          CA060129020      220060110G7321                FUEL CONTROL                            PILATSPC12  PC12        7090550EU  PWA   PT6   PT6A67B     52043NE                              ENGINE          FAULTED         W      D   RETURN TO BLOCK                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA                                                                      DURING TAXI, THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION.  THE ENGINE WAS SHUT DOWN.  SUBSEQUENT INSPECTION REVEALED A FAULTY FUEL CONTROL UNIT.  P&WC WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L71 3T4  TRTA78EU   E26NE                
20060703000522006070300052NE  2006       7          3          CA060129021      220060121G7200                ENGINE                                  AEROSPATR72 ATR72212A   8680902EU  PWA   PW120 PW127            NE                                              POWER LOSS      W      E   ENGINE SHUTDOWN                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA                                          AV0032                      DURING CRUISE, ENGINE EXPERIENCED AN UNCOMMANED POWER REDUCTION.  THE ENGINE WAS SHUT DOWN IN FLIGHT.  PWC WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2H72 4T4  TRTA53EU   E20NE                
20060703000532006070300053WP  2006       7          3          CA060130001      120060116G6321E02400373500S   SPRING          ROBSIN                  ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              ROTOR BRAKE     BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       92         10913                                               DURING THE FIRST 100 HR INSPECTION CARRIED OUT ON THE AIRCRAFT, IT WAS NOTICED THAT THE ABOVE SPRING WAS BROKEN.  IT APPEARS TO HAVE BROKEN AT THE UPPER ATTACHMENT POINT WHERE IT ATTACHES TO THE LOWER ROTOR BRAKE CALIPER ARM.  THE SPRING WAS REPLACED WITH NEW.                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1G71 3O3  O  H11NM   1E4                  
20060703000542006070300054CE  2006       7          3          CA060130002      120060125G5610                WINDSCREEN                              BEECH 90    C90A        1152911CE  PWA   PT6   PT6A21      52043EA  HARTZLHCB3T HCB3TN3     GL  COCKPIT         FAILED          W      B   EMER. DESCENT                                                                                   O  OTHER                                                                         CRCRUISE         1                      CA                                                                      WHILE IN CRUISE FLIGHT AT FL230, THE LT WINDSHIELD INNER PANE SHATTERED.  THE WINDSHIELD ANTI-ICE HAD BEEN SELECTED AT NORMAL SINCE DEPARTURE AND THE OAT WAS 38C.  THE CREW CONTACTED ATC TO DECLARE AN EMERGENCY AND REQUESTED RETURN TO AIRPORT.  THE CREW THEN COMPLETED THE CRACKED OR SHATTERED WINDSHIELD CHECKLIST.  AS A PRECAUTION, THE OXYGEN MASKS WERE DONNED BY THE CREW MEMBERS AND PASSENGERS.  THE CAPTAIN FLEW THE APPROACH AND THE CO-PILOT FLEW THE DESCENT TO VISUAL AND LANDED SAFELY ON RWY 06.                                                                                                                                                                                                                        1L72 3T4  TRT3A20    E4EA    6  CP15EA    
20060703000552006070300055NE  2006       7          3          CA060130003      220060116G72503053094CL9      SHROUD                                  BEECH 90    F90         1152909CE  PWA   PT6   PT6A135     52043NE  HARTZLHCB4T HCB4TN3     GL  HOT SECTION     DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1245                                                           ROUTINE BOROSCOPE INSPECTION OF HOT SECTION COMPONENTS REVEALED THAT TWO CT SEGMENTS HAD DROPPED OUT OF PLACE AND CONTACTED CT WHEEL.  THE SEGMENT RETAINING RING P/N 3020139 WAS FOUND OUT OF PLACE AND THE CT BLADES HAD WORN BEYOND LIMITS DUE TO HEAVY TIP RUB.  THE WHEEL WAS REBLADED AND SEGMENTS REPLACED WITH P/N 3035673CL12 AND RETAINING RING P/N 3110741-02, SB1627 AND SB1628 WERE EMBODIED.                                                                                                                                                                                                                                                                                                                                      1L72 4T4  T  A31CE   E4EA    6  CP40EA    
20060703000562006070300056NE  2006       7          3          CA060130004      220060116G72503053094CL14     SHROUD                                  BEECH 90    F90         1152909CE  PWA   PT6   PT6A135     52043NE  HARTZLHCB4T HCB4TN3     GL  HOT SECTION     DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1666                                                           ROUTINE BOROSCOPE INSPECTION OF HSI COMPONENTS FOUND TWO SEGMENTS HAD DROPPED OUT OF POSITION.  POWER SECTION REMOVED AND CT COMPONENTS INSPECTED.  CT BLADES FOUND TO HAVE CONTACTED SEGMENT ENDS AND RETAINING RING P/N 3020159 FOUND OUT OF PLACE.  SEGMENTS REPLACED WITH NEW P/N 3053094CL16 AND NEW RETAINING RING P/N 3020159 AND ALTERNATE SEGMENTS AND RING NOT AVAILABLE IN THE REQUIRED CLASS.  ENGINE REASSEMBLED.  SB1627 EMBODIED.                                                                                                                                                                                                                                                                                                1L72 4T4  T  A31CE   E4EA    6  CP40EA    
20060703000572006070300057CE  2006       7          3          CA060130005      120060124G5344                HINGE                                   BEECH 200   B200        1152922CE  PWA   PT6   PT642A           NE  HARTZLHCE4N HCE4N3      NE  CABIN DOOR      FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA       598                                                            CABIN DOOR SIDE OF HINGE WAS REPLACED ON MARCH 15 2005 AT 5248.4 TTAF AND 4829 CYCLES.  DOOR SIDE OF HINGE FAILED JAN 23 2006 AT 5846.8 TTAF AND 5480 CYCLES DOOR AND HINGE AREA WAS INSPECTED AND NO ADDITIONAL DAMAGE WAS NOTED CHERRYMAX RIVETS WHICH WERE INSTALLED WERE FOUND TO BE INCORRECT SIZE.  RECTIFICATION WAS TO REPLACE CHERRYMAX RIVETS WITH SOLID RIVETS.                                                                                                                                                                                                                                                                                                                                                                      1L72 4T4  T  A24CE   E4EA    5  CP10NE    
20060703000582006070300058EA  2006       7          3          CA060131001      120060124G2497                WIRE HARNESS                            CNDAIRCL600 CL6002C10   1390015EA                                                                               DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       6607                                                           DURING T/S OF INOP LAV LIGHTS, FOUND 6 WIRES BELOW FLOOR, RT SIDE AFT FWD SERVICE DOOR DAMAGED, BURNED.  SMALLER HARNESS IS ROUTED UNDER LARGER HARNESS.  TWO BUNDLES WERE NOT SECURED AND THIS ALLOWED 2 HARNESSES TO RUB UNTIL CENTER CONDUCTORS EXPOSED AND A POWER AND GROUND MADE CONTACT RESULTING IN BLACK RESIDUE ON THE HARNESSES.  WIRING WAS REPLACED AND HARNESS SECURED TO ELIMINATE THE FOULING.  FOLLOWING WIRES ARE DAMAGED, OUTER JACKET DAMAGE WIRE NO ATA SYSTEM FBF7941-22 28-40-00, REFUEL/DEFUEL PANEL FBG6885-18 33-21-00, RT CEILING LT DIM/BRT FBG6884-18 33-21-00, RT CEILING LT DIM CONTROL CORE EXPOSED WIRE NO ATA SYSTEM FBF6420-22 33-24-00, FASTENER SEAT BELT SIGN FBH6770-22 33-22-00, PSU TEST FBH6771-22 33-2L72 4F    RTA21EA                        
20060703000592006070300059EU  2006       7          3          CA060131002      120060127G21605829C00         CONTROLLER                              PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  CABIN TEMP      FAILED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      CA            810                                                       PILOT SELECTED ENVIRONMENTAL SYSTEMS TO AUTO PRIOR TO FLIGHT AND RECEIVED A CAUTION LIGHT ON PANEL THAT THE SYSTEM WAS NOT FUNCTIONING.  THE SYSTEM WAS CYCLED ON AND OFF THEN AN INCREASE IN POWER WAS APPLIED AND THE CAUTION LIGHT EXTINGUISHED INDICATING NORMAL. FURTHER FLIGHTS THAT DAY WERE UNEVENTFUL. MAINTENANCE TROUBLESHOOTING VIA THE MANUAL SWITCH FROM FULL COLD THEN FULL HOT RESULTED IN A STUCK IN HOT VALVE.  THE TEMP VALVE WAS REPLACED AND SYSTEM FUNCTIONED FINE.  AIRCRAFT TTSN 4650HRS,CYC 3286, THE ORIGINAL VALVE WAS REPLACED AT 3837 HRS 2662 CYC.  THE ONE REPORTED FAILED AT 810 HRS AND 622 CYC.                                                                                                               1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20060703000962006070300096CE  2006       7          3          CA060131003      120060120G2823S160315865      CABLE                                   CESSNA337   337C        2075712CE  CONT  O360  IO360C      17025SO                              FUEL SELECTOR   BENT            W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      AIRCRAFT WAS IN CRUISE FLT WHEN THE PILOT ATTEMPTED TO CHANGE LT FUEL SELECTOR FOR FORWARD ENGINE TO A DIFFERENT TANK.  WHEN SELECTED THE KNOB STOPPED AT THE 1/2 WAY POINT CAUSING FUEL FLOW AND ENGINE POWER TO DECREASE.  THE PILOT SHUT DOWN THE ENGINE AND CONTINUED TO BASE WITHOUT FURTHER INCIDENT.  UPON MAINTENANCE INSPECTION, THE SELECTOR CABLE WAS FOUND KINKED.  THE SELECTOR MECHANISM AND SELECTOR KNOB MECHANISM WERE BOTH FOUND TO MOVE FREELY.  NO OTHER DISCREPENCIES FOUND.  NEW CABLE BEING INSTALLED.                                                                                                                                                                                                                   1H72 3O3  O  A6CE    E1CE                 
20060705000272006070500027SW  2006       7          5          CA060131004      120060127G6730AN8345D         TEE FITTING                             BELL  206   206B        1181511SW  ALLSN 250C  250C20      03013GL                              SERVO ACTUATOR  CRACKED         W      HA  DEACTIVATE SYST/CIRCUITSUNSCHED LANDING                                                         F  FLT CONT AFFECTED                                                             CRCRUISE         1                      CA                  3153                                                WHILE IN CRUISE FLIGHT, THE PILOT FELT FEEDBACK SHOCK IN THE CYCLIC CONTROL.  THE PILOT ISOLATED HYDRAULICS AND MADE AN UNSCHEDULED LANDING.  MAINTENANCE CREW PERFORMED AN INSPECTION OF THE HYDRAULIC FLIGHT CONTROL SYSTEM.  A TEE FITTING THE LEFT HAND SERVO ACTUATOR WAS FOUND CRACKED AROUND HALF IT'S DIAMETER RESULTING IN A LEAK.                                                                                                                                                                                                                                                                                                                                                                                                     1G71 3U3  U  H2SW    E4CE                 
20060705000302006070500030GL  2006       7          5          CA060131005      220060120G725023001967        TURBINE WHEEL   ALLSN       6898735                                        ALLSN 25OC  250C20R          GL                              ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       819        CAT25545                                            TURBINE RECEIVED AT ETI FOR REPAIR.  NR 3 TURBINE WHEEL INSPECTED ON TEARDOWN.  NR 3 TURBINE WHEEL SENT TO NDT FOR FPI.  CRACKS WERE FOUND ON RIM.  LOG CARDS SHOW THAT NR 3 TURBINE WHEEL (S/N HX-84-131) HAS TTSN: 819.1 AND TCSN: 770.  NR 3 TURBINE WHEEL LIFE IS TT: 4450 ^ TC: 6000.                                                                                                                                                                                                                                                                                                                                                                                                                                                             3  U          E4CE                 
20060705000362006070500036CE  2006       7          5          CA060201001      120060201G571112212352        SPAR                                    CESSNA210   T210N       2073456CE  CONT  O520  TSIO520R    17040SO  MCAULYD3A34 D3A34C402   GL  RT WING         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3861 3861                                                      A 100 HR INSPECTION WAS STARTED A CRACK WAS DISCOVERED AT THE RIGHT FRONT SPAROUT BOARD END WHERE IT ATTACHES TO THE SUB SPAR.  THE CRACK IS VERTICAL RUNNING APPROXIMATELY 1 1/2 TO TWO INCHES IN LENGTH.  THE CRACK STARTS AT THE TOP AND RUNS DOWN THROUGH A RIVET AND CONTINUES ON.                                                                                                                                                                                                                                                                                                                                                                                                                                                         1H71 3O3  O  3A21    E8CE    5  CP47GL    
20060705000372006070500037GL  2006       7          5          CA060201002      320060201G6111                BEARING         HARTZL      HC83V202C   GRUMAVSTC   STCSCANTY30                                             HARTZLHC83V HC83V202    GL  PROPELLER       CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      UPON MPI INSPECTIONS, IT WAS NOTED THAT 2 A14B BEARINGS, 2 C838-6 CLAMPS, 1 C1404 HUB, AND 1 A1496-0 ARM WERE ALL CORRODED BEYOND LIMITS.  THROUGH DIMENSIONAL INSPECTIONS THE FOLLOWING PARTS WERE FOUND TO BE WORN BEYOND SERVICEABLE LIMITS, 1 B806 CYLINDER AND ONE A871 MUSHROOM.                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H72 3I      A734            5  CP14EA    
20060705000382006070500038GL  2006       7          5          CA060201003      320060201G6111                CLAMP           HARTZL      HC83V202C   GRUMAVSTC   STCSCANTY30                                             HARTZLHC83V HC83V202    GL  PROPELLER       CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                  D1629                                               UPON MPI INSPECTION IT WAS NOTED THAT 2 A14B BEARINGS, 3 C838-6 CLAMPS, 1 C1404 HUB, AND 2 A1496-0 ARMS WERE ALL CORRODED BEYOND LIMITS.  THROUGH DIMENSIONAL INSPECTIONS THE FOLLOWING PARTS WERE FOUND TO BE WORN BEYOND SERVICEABLE LIMITS,1 B806 CYLINDER AND 1 A871 MUSHROOM.                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H72 3I      A734            5  CP14EA    
20060705000392006070500039CE  2006       7          5          CA060201004      120060129G53441154400311      HINGE BRACKET                           BEECH 100   100BEECH    1152916CE  PWA   PT6   PT6A28           EA                              FUSELAGE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      A 3/4 INCH CRACK WAS DISCOVERED WHEN MAINTENANCE WENT TO CHANGE A BUSHING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L72 3T4  T  A14CE   E4EA                 
20060705000402006070500040CE  2006       7          5          CA060202001      120060131G5297                WIRE                                    BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE  HARTZLHCE4A HCE4A3I     NE  CARGO BAY       CHAFED          W      K   NONE                                                                                            N  FALSE WARNING                                                                 ININSP/MAINT     1                      CA                                                                      A/C BROUGHT INTO HANGAR AFTER THE DAY OF FLYING.  WHILE IN THE HANGAR THE CARGO DOOR WARNING CAME ON.  INSPECTED THE DOOR WARNING AND FOUND THE DOOR AJAR SWITCH STICKY AND THE LATCH HANDLE SWITCH CRACKED.  SWITCHES REPLACED ALL CHECKED OK.  THE REASON FOR THIS SDR IS THAT DURING THE INSPECTION OF THE CARGO DOOR ELECTRICAL SYSTEM FOUND THAT THE LOWER WIRING HAS BEEN CHAFING ON THE DOOR. THIS COULD POSSIBLE CAUSE ERRONEOUS INDICATIONS IN THE FUTURE. SPIRAL WRAP WAS PLACED ON THE WIRING AND WIRING RESECURED TO TYWRAP POINTS.  WOULD SUGGEST THAT THIS WIRING BE SPIRAL WRAPPED TO PREVENT THIS FROM CAUSING A FAULT IN THE FUTURE.                                                                                           2L72 4T4  TRTA24CE   E26NE   5  CP10NE    
20060705000412006070500041NE  2006       7          5          CA060202002      220060201G7261                OIL SYSTEM                              AEROSPATR42 ATR42300    8680920EU  PWA   120   PW120            NE  HAMSTD14SF  14SF5       NE  NR 1 ENGINE     LEAKING         W      E   ENGINE SHUTDOWN                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      AFTER DEPARTING, THE CREW OBSERVED LOSS OF OIL PRESSURE ON NR 1 ENGINE.  THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WITHOUT FURTHER INCIDENT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2H72 4T4  TRTA53EU   E20NE   6  CP7NE     
20060705000432006070500043NM  2006       7          5          CA060202003      120060129G2910                HYDRAULIC LINE                          BOEING737   737522      138449FNM  CFMINTCFM56 CFM563C1    13802EU                              THRUST REVERSER CHAFED          W      K   NONE                                                                                            K  FLUID LOSS                                                                    NRNOT REPORTED   1                      CA                                                                      HYDRAULIC LEAK DISCOVERED ON STOW LINE TO LT INBOARD THRUST REVERSER SYNC ACTUATOR ON NR 2 ENGINE, CAUSED FROM RUBBING ON AN ANGLE EDGE SUPPORT.  LINE REMOVED AND FITTINGS CAPPED.  A FLEET CAMPAIGN IS NOW IN PROGRESS TO CHECK ALL SYNC ACTUATOR LINES FOR DAMAGE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F4  FRTA16WE   E21EU                
20060705001112006070500111SO  2006       7          5          CA060202004      120060118G71208621202         MOUNT                                   PIPER PA44  PA44180     7104402SO  LYC   O360  O360E1A6    41514EA  HARTZLHCC2Y HCC2YR2     GL  LEFT ENGINE     CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       8436                                                           WHILE CARRYING OUT SCHEDULED 100 HOUR INSPECTION ON LEFT ENGINE A CRACK ON THE LT ENGINE MOUNT TOP OUTBOARD SECTION WAS NOTED.  MOUNT WAS REMOVED, REPAIRED AND REINSTALLED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L72 3O3  O  A19S0   E286    5  CP920     
20060705001132006070500113    2006       7          5          CA060202005      420060201G2330                VIDEO DISPLAY                           BOEING737   737*               NM  CFMINTCFM567CFM567B22   13802NE                              SEAT 3C         MALFUNCTIONED   W      H   DEACTIVATE SYST/CIRCUITS                                                                        B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA                                                                      A/C WAS IN CRUISE WHEN THE VDU AT SEAT 3C WENT BLANK FOLLOWED BY A SLIGHT ELECTRICAL SMELL. THE IFE SYSTEM WAS DEACTIVATED.  MAINTENANCE PLACED THE VDU ON MEL.  THIS SDR WILL HAVE THE DEFECTIVE COMPONENT PART NUMBER AND SERIAL NUMBER UPDATED WHEN THAT INFORMATION IS AVAILABLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F4  FRTA16WE   E00055EN             
20060705001142006070500114SW  2006       7          5          CA060202006      120060201G5320206031106079    ANGLE                                   BELL  206   206B3       1181506SW                                                               FUSELAGE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       11601                                                          ANGLE FROM VERTICAL TUNNEL TO BOX BEAM CRACKED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1G71 3U      H2SW                         
20060705001152006070500115NE  2006       7          5          CA060203001      220060201G73108280127119      FUEL LINE                               DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  LT ENGINE       DAMAGED         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      IT WAS DISCOVERED DURING OVERNIGHT ROUTINE MAINTENANCE THAT THE FUEL LINE IN THE LT ENGINE COMPARTMENT HAD BEEN IN CONTACT WITH A BRAIDED SHIELDED WIRE HARNESS CAUSING SEVERAL PIN HOLES WITHIN THE FUEL LINE CAUSING AN ATOMIZING EFFECT OF THE FUEL WITHIN THE ENGINE NACELLE.  FUEL LINE WAS REPLACED AND WIRE HARNESS RESECURED TO ENSURE TO CONTACT WITH FUEL LINE.  AIRCRAFT GROUND RUN AND RELEASED INTO SERVICE.                                                                                                                                                                                                                                                                                                                       2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060705000832006070500083SO  2006       7          5          CA060203003      120060129G3297                WIRE HARNESS    PIPER       4550402     PIPER PA31  PA31350     7103110SO  LYC   O540  TIO540J2BD  41532EA  HARTZLHCE3Y HCE3YR2A    GL  MLG             BROKEN          W      O   OTHER                                                                                           P  NO WARNING INDICATION                                                         APAPPROACH       1                      CA                                                                      (CAN) WHEN LANDING GEAR WAS SELECTED ON APPROACH THE LT GEAR DOWN AND LOCKED LIGHT DID NOT COME ON.  CREW CHECKED THE BULB AND NOTIFIED AIR RADIO OF THE SITUATION. A FLY PAST WAS CARRIED OUT AND THE GEAR WAS CONFIRMED TO BE DOWN AND LOCKED. THE AIRCRAFT LANDED AND THE GEAR WAS INSPECTED FOR THE PROBLEM, A BROKEN WIRE WAS IDENTIFIED AND REPAIRED. (TC NR 20060203003)                                                                                                                                                                                                                                                                                                                                                                 1L72 3O3  O  A20SO   E14EA   5  CP33EA    
20060608003862006060800386EA  2006       6          8          CA060203004      220060130G8500                ENGINE                                  PIPER PA31  PA31350     7103110SO  LYC   O540  TIO540J2BD  41532EA  HARTZLHCE3Y HCE3YR2A    GL  RIGHT           FAILED          W      A   UNSCHED LANDING                                                                                 Y  ENGINE STOPPAGE                                                               CRCRUISE         1                      CA            2272                                                      DURING CRUISE FLIGHT, THE CREW HAD A SUDDEN LOSS OF POWER ON THE RIGHT HAND ENGINE.  THE ENGINE WAS FEATHERED AND THE AIRCRAFT WAS DIVERTED TO THE NEAREST AIRPORT.  AFTER LANDING THE ENGINE WAS INSPECTED FOR ANY EXTERNAL DAMAGE OR OIL LEAKS NONE WERE FOUND.  OIL FILTER WAS REMOVED, METAL WAS FOUND SO FLIGHT WAS TERMINATED AND ENGINE ORDERED.                                                                                                                                                                                                                                                                                                                                                                                         1L72 3O3  O  A20SO   E14EA   5  CP33EA    
20060608003872006060800387CE  2006       6          8          CA060203005      120060131G5544AD200020        STOP                                    CESSNA150   150F        2071814CE  CONT  O200  O200A       17020SO  MCAULY1A100 1A100MCM    GL  RUDDER          FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      NO JAMMING OR EVIDENCE OF SEE ON EITHER RUDDER STOPS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1H71 3O3  O  3A19    E252    5  NP918     
20060608003882006060800388NM  2006       6          8          CA060203006      120060129G276082740061020     CLUTCH                                  BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                              RT SPOILER      UNKNOWN         W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             TXTAXI/GRND HDL  1                      CA       326                                                            FLIGHT CREW FOUND THEY COULD NOT OPERATE THE CONTROL WHEEL CCW DIRECTION AFTER ENGINE STARTING.  THE FLIGHT WAS CANCELLED.  MAINTENANCE FOUND THE MICROSWITCH ON THE RT SPOILER CLUTCH ASSY CONTACTING WITH THE BRACKET-UPPER MOUNTING.  THE CONTACT WAS CAUSED BY THE IMPROPER INSTALLATION OF THE MICROSWITCH SCREWS.  BOMBARDIER AEROSPACE IS INVESTIGATING THIS EVENT.                                                                                                                                                                                                                                                                                                                                                                      2H72 4T4  TRTA13NM   E00062EN             
20060608003892006060800389CE  2006       6          8          CA060203007      120060202G2701126011131       GUARD                                   CESSNA206   T206H       2073303CE                                                               AILERON CABLE   LOOSE           W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       14                                                             WHILE INSTALLING ALTERNATOR/WIRING UPGRADE, IT WAS NOTICED THAT THE STRAP COVER WAS LOOSE ON THE CABLE GUARD ON THE LEFT SIDE AILERON CONTROL QUADRANT.  SUBSEQUENT INSPECTION REVEALED THE RIGHT SIDE WAS ALSO LOOSE.  TOP AND BOTTOM SCREWS ON THE LEFT AND RIGHT SIDE WERE TOO SHORT DUE TO A WASHER BEING PLACED IN BETWEEN THE STRAP COVER AND THE AILERON CABLE GUARD FROM THE FACTORY.   INSUFFICIENT THREAD DEPTH INTO NUTPLATE, IE: 2 THREADS HOLDING ALL 4 FASTENERS = NOT IN SAFETY.  A CONDITION REPORT WAS SENT TO THE CESSNA FIELD REP TO INVESTIGATE QUALITY CONTROL ISSUES IN REGARDS TO THE POSSIBILITY OTHER NEW A/C AFFECTED.                                                                                                1H71 3O    RTA4CE                         
20060608003902006060800390CE  2006       6          8          CA060205001      120060202G249710936102247     WIRE                                    BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE  HARTZLHCE4A HCE4A3I     NE  DC POWER        BURNED          W      D   RETURN TO BLOCK                                                                                 O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA                                                                      ON START, THE CREW ATTEMPTED TO START THE RIGHT ENGINE.  BUT NO LUCK STARTING THE ENGINE.  AIRCRAFT BROUGHT TO HANGAR AND MAINTENANCE DISPATCHED.  UPON ARRIVAL, MAINTENANCE ATTEMPTED TO START THIS ENGINE.  NO JOY.  THE STARTING ONLY HAD APPROX 300 HOURS REMAINING TIL OVERHAUL THEREFORE MAINTENANCE REPLACED THE STARTER THINKING THIS WOULD BE THE FAULT.  THE STARTER GENERATOR WAS NOT THE FAULT.  INSPECTION REVEALED THAT THE STARTER CABLE FEED THRU WAS BURNT UP ALONG WITH THE DC POWER PANEL.  THE STARTER LUG.  REPLACED THE FEED THRU CABLE AND THE POWER PANEL AND ENGINE START AND RUNS CARRIED OUT.  NOW CHECKING SERVICEABLE.                                                                                             2L72 4T4  TRTA24CE   E26NE   5  CP10NE    
20060608003912006060800391NM  2006       6          8          CA060206001      120060129G3297471509          WIRE HARNESS                            BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                              NLG WOW         UNKNOWN         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      CA                                                                      AN AIRCRAFT EXPERIENCED INTERMITTENT WOW CAUTION LIGHT DURING FLIGHT.  MAINTENANCE TELL US THAT THERE IS NO CURRENT FAULT TO BE FOUND IN THE PSEU NVM.  HOWEVER, THE NLG WOW 1 SENSOR SHOWS A HISTORY OF FAULTS IN RIGGING HISTORY.  WOW 1 SENSOR HARNESS IN NLG REPLACED.  A/C RTS.                                                                                                                                                                                                                                                                                                                                                                                                                                                            2H72 4T4  TRTA13NM   E00062EN             
20060608003922006060800392NM  2006       6          8          CA060206004      120060129G3297471515          WIRE HARNESS                            BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                              NLG WOW         UNKNOWN         W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CRCRUISE         1                      CA                                                                      AN AIRCRAFT EXPERIENCED AN INTERMITTENT WOW CAUTION LIGHT DURING FLIGHT.  MAINTENACE PERSONNEL FOUND THAT THERE IS NO CURRENT FAULT TO BE FOUND IN THE PSEU NVM.  HOWEVER, THE LT GEAR WOW 2 SENSOR SHOWS A HISTORY OF FAULTS IN FAULT HISTORY.  WOW NR 2 HARNESS IN NLG REPLACED.  A/C RTS.                                                                                                                                                                                                                                                                                                                                                                                                                                                    2H72 4T4  TRTA13NM   E00062EN             
20060608003932006060800393NM  2006       6          8          CA060206007      120060129G3297471515          WIRE HARNESS                            BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                              NLG CENTERING   UNKNOWN         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA                                                                      AN AIRCRAFT HAD TO RETURN TO FIELD BECAUSE OF FAILURE OF THE LANDING GEAR TO RETRACT.  UPON INVESTIGATION AND INTERROGATION OF THE PSEU THE FAULT CODES WERE UNREASONABLE FAR -00.  NLG WOW 2/CENTERING HARNESS REPLACED.  A/C RTS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2H72 4T4  TRTA13NM   E00062EN             
20060608003942006060800394NM  2006       6          8          CA060206008      120060201G3297471515          WIRE HARNESS                            BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                              NLG             UNKNOWN         W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CRCRUISE         1                      CA                                                                      AN AIRCRAFT EXPERIENCED A WOW CAUTION LIGHT DURING FLIGHT.  MAINTENANCE FOUND PSEU INDICATED NR 2 WOW UNREASONABLE FAR, WITH TARGET PLACED IN FRONT OF SENSOR, THERE WAS NO CHANGE.  THE TECHNICIANS CHANGED THE NLG NR 2 WOW HARNESS PER AMM 32-21-11-400-801, AND PSEU SHOWS NO FAULTS.  A/C RTS.                                                                                                                                                                                                                                                                                                                                                                                                                                             2H72 4T4  TRTA13NM   E00062EN             
20060608003952006060800395NM  2006       6          8          CA060206009      120060203G3230483023          SEQUENCE VALVE                          BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                              NLG DOOR        MALFUNCTIONED   W      O   OTHER                                                                                           O  OTHER                                                                         DEDESCENT        1                      CA                                                                      DURING DESCENT, THE NLG DID NOT EXTEND UNDER NORMAL EXTENSION, ALTERNATE RELEASE USED.  MAINTENANCE REPLACED THE NLG DOOR SOLENOID SEQUENCE VALVE, CONDUCTED HYD BLEEDING AND GEAR SWINGS.  A/C RTS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2H72 4T4  TRTA13NM   E00062EN             
20060705001752006070500175NM  2006       7          5          CA060206010      120060203G3260471515          WIRE HARNESS                            BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  NLG             FAILED          W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      CA                                                                      (CAN) AFTER TAKEOFF THE GEAR FAILED TO RETRACT UPON GEAR UP SELECTION. MAINTENACE FOUND NWCENT OPEN ON THE PSEU. NLG WOW 2/ CENTERING HARNESS REPLACED. A/C RTS. (TC NR 20060206010)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
20060705001772006070500177NM  2006       7          5          CA060206012      120060128G2740106054554       BEARING RACE                            BOEING737   737275C            NM  PWA   JT8   JT8D9A      52048NE                              ELEVATOR MAST   WORN            W      A   UNSCHED LANDING                                                                                 F  FLT CONT AFFECTED                                                             CLCLIMB          1                      CA                                                                      (CAN) LOW FREQUENCY OSCILLATION FELT THROUGH AIRFRAME DURING CLIMB BETWEEN 240-270 KTS. NO CHANGE WITH AUTOPILOT ON OR OFF.  ( NOTE: THIS WAS NOT VIBRATION ) HORIZ STAB PIVOT BEARINGS ON BOTH THE LT AND RT SIDE WERE REPLACED, BEARING HOUSING WAS REPLACED ON LT SIDE . ELEVATOR INPUT BEARINGS ON ELEVATOR MAST WERE REPLACED BOTH LT AND RT SIDE.     FOLLOW UP ACTION THERE HAS BEEN A HARD FAILURE FOUND. COMPONENTS HAVE BEEN REPLACED. THERE IS NO FOLLOW UP REQUIRED.   AC REMOVED FROM SERVICE FOR HORIZONTAL PIVOT BEARING REPLACEMENT.                                                                                                                                                                                            2L72 4F4  F  A16WE   E2EA                 
20060705001792006070500179CE  2006       7          5          CA060207001      120060130G322257411501        AXLE                                    CESSNA441   441         2076020CE  GARRTTTPE331TPE33110    01514WP  HARTZLHCB3T HCB3TN5     GL  NLG             CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       9824                                                           (CAN) THE FORK, AXLE ASSY WAS SENT TO SHOP FOR BUSHING REPLACEMENT, INPECTION AND PAINTING. THEY FOUND THE AXLE BACK PLATE CRACKED. NEW AXLE FITTED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L72 3T4  TRTA28CE   E4WE    6  CP15EA    
20060705001802006070500180CE  2006       7          5          CA060207002      120060207G2720504200337       SUPPORT BEAM                            BEECH 100   A100        1152915CE  PWA   PT6   PT6A28           EA  HARTZLHCB4T HCB4TN3     GL  RUDDER QUAD     CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2646926469                                                     (CAN) UNDER THE PILOTS FLOOR BOARDS AT FLIGHT STATION 107 THE PILOTS RUDDER QUADRANT SUPPORT BEAM WAS FOUND CRACKED. THESE CRACKS WERE FOUND AT THE TOP BEND RADIUS AND AT SOME HOLES FOR NUT PLATES. WE HAVE FOUND THESE SAME CRACKS ON 3 OTHER OF OUR AIRCRAFT AROUND THE SAME LOCATIONS. THE BEAM WAS REPLACED AND CHECKED SERVICABLE (TC NR 20060207002)                                                                                                                                                                                                                                                                                                                                                                                    1L72 3T4  T  A14CE   E4EA    6  CP40EA    
20060705001812006070500181NM  2006       7          5          CA060207003      120060207G323146503105        TARGET                                  BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  MLG UPLOCK ASSY MISSING         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA       345                                                            (CAN) AFTER THE LANDING GEAR SELECTED TO UP DURING CLIMB, THE LT DOOR AMBER INDICATION REMAINED ON AS WELL AS THE LT MLG RED INDICATOR REMAINED ON.  CREW RETURNED TO BASE.  MAINTENANCE FOUND:  LT UP-LOCK SENSOR INDUCTANCE REPORTED TO BE OUT OF LIMITS. THE LOW INDUCTANCE FOR THE UP-LOCK SENSOR HAS BEEN TRACED TO A MISSING TARGET ON THE UP-LOCK. MLG UPLOCK ASSY TO BE REPLACED. (TCNR 20060207003)                                                                                                                                                                                                                                                                                                                                    2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
20060705001822006070500182GL  2006       7          5          CA060207004      320060205G61124E256010        BOOT            HARTZL                  CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE  HARTZLHCB3T HCB3TN3     GL  PROPELLER       MISSING         W      A   UNSCHED LANDING                                                                                 E  VIBRATION/BUFFET                                                              CRCRUISE         1                      CA       344        BUA27749                                            (CAN) WHILE ON A ROUTINE LOCAL TRAINING FLIGHT, THE PILOT EXPERIENCED SEVERE VIBRATION FROM THE ENGINE/PROPELLER. RETURNING TO THE AIRFIELD THE AIRCRAFT WAS LANDED SAFELY. INSPECTION REVEALED THAT ONE PROPELLER BLADE DE-ICER BOOT HAD DETACHED FROM THE BLADE AND WAS MISSING. THE MISSING BOOT HAD BEEN INSTALLED ON SEPT 9/2005 AND HAD ACCRUED 343.7 HRS TSN. (TC NR 20060207004)                                                                                                                                                                                                                                                                                                                                                        1H71 3T3  T  A37CE   E4EA    6  CP15EA    
20060705001832006070500183CE  2006       7          5          CA060207005      120060207G32220641124         AXLE                                    CESSNA305   305A        2074002CE  CONT  O470  O47011      17026SO  MCAULY1A200 1A200*      GL  MLG             CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       4331 4331                                                      (CAN) DURING A STRUCTURAL INSPECTION, A CRACK WAS FOUND IN RADIUS OF PART WHERE THE CYLINDER PORTION MEET THE BLOCK WHERE THE BOLTS ARE. BOTH AXLES (QTY 2) WERE CRACKED. ONE WAS VERY EASY TO SEE. THE OTHER APPEARED UNDER LIQUID PENETRANT. PARTS HAVE BEEN REPLACED BY NEW PARTS.  DND HAVE A SPECIAL INSPECTION ON THAT PART FOR THE MFG OPERATED BY THE MILITARY. SOME WERE FOUND WITH CRACKED AXLES 3 YEARS AGO. (TC NR 20060207005)                                                                                                                                                                                                                                                                                                     1H71 3O3  O  5A5     E269    5  NP874     
20060705001842006070500184EA  2006       7          5          CA060208001      120060130G76031603730007      THROTTLE CABLE                          CNDAIRCL600 CL6002B19   1900309EA                                                               COCKPIT         BROKEN          W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         F  FLT CONT AFFECTED                                                             CRCRUISE         1                      CA       11003                                                          (CAN) THE LT ENGINE WOULD NOT GO BELOW 82 PERCENT WHEN THE THROTTLE WAS RETARDED TOWARD IDLE. THE LT ENGINE WAS SHUT DOWN IAW QRH INSTRUCTION. TROUBLESHOOTING REVEALED THE CABLE ASSEMBLY FROM THE GEARBOX TO MFC BROKEN. CABLE WAS REPLACED IAW AMM. (TC NR 20060208001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F    RTA21EA                        
20060705002142006070500214EA  2006       7          5          CA060208002      120060119G27306224404101      CONTROL CABLE                           CNDAIRCL600 CL6002C10   1390015EA                                                               ELEVATOR        STUCK           W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA       2991                                                           (CAN) DURING APPROACH ELEVATOR CONTROL STUCK MOMENTARILY. APPROX 5 LB CONTROL FORCE BROKE ELEVATOR CONTROL FREE. ELEVATOR CONTROL OPERATED NORMALLY FOR APPROACH AND LANDING.  AUTO PILOT PITCH SERVO CONDITION AND CABLE TENSION, PERFORMING A SLIP CLUTCH CHECK OF THE PITCH SERVO MOUNT, PERFORM OPERATIONAL CHECK OF THE AUTOPILOT SYSTEM. ALSO COMPLETED LUBRICATION OF THE ELEVATOR SERVO IAW REQUEST.  ALL CHECKS WERE GOOD AND LUBRICATION COMPLETED (TC NR 20060208002)                                                                                                                                                                                                                                                                2L72 4F    RTA21EA                        
20060705002402006070500240SO  2006       7          5          CA060208003      120060207G322167054003        TRUNNION                                PIPER PA44  PA44180     7104402SO  LYC   O360  O360E1A6    41514EA  HARTZLHCC2Y HCC2YR2     GL  NLG             CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       6857                                                           (CAN) PART OF THE INSPECTION PROGRAM INCLUDES LANDING GEAR SERVICING. THE GEAR TRUNNIONS ARE FITTED WITH GREASE HOLES AND/OR FITTINGS TO ALLOW QUICK AND EASY SERVICING DURING SCHEDULED INSPECTIONS. WHILE CARRYING OUT THIS SERVICING ON THE NOSE GEAR TRUNNION GREASE WAS NOTED COMING OUT OF AN ODD LOCATION. PAINT WAS STRIPPED FROM THE LOWER KNUCKLE AND REVEALED CRACKS TOP AND BOTTOM.  A SERVICEABLE INSPECTED UNIT WAS INSTALLED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20060208003)                                                                                                                                                                                                                                               1L72 3O3  O  A19S0   E286    5  CP920     
20060705002412006070500241EU  2006       7          5          CA060208004      120060208G276070282721801     MODULE                                  EMB   ERJ190ERJ190100IGW3260408EU                                                               SPOILERS        FAULTY          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) SPOILER FAULT CAUTION AT 33000. THE AIRCRAFT DID YAW AS A SPOILER PANEL EXTENDED AND RETRACTED. QRH PROCEDURES CARRIED OUT. SPOILERS CONFIRMED RETRACTED VISUALLY FROM CABIN. IB MULTIFUNCTION SPOILERS INDICATED A FAULT ON MFD FLIGHT CONTROL  PAGE FLT CTRL NO DISPATCH AFTER LANDING. ACTION: FLIGHT CONTROL MODULE REPLACED IAW AMM 27-03-02 (TC NR 20060208004)                                                                                                                                                                                                                                                                                                                                                                     2L72 4F    RTA57NM                        
20060705002422006070500242GL  2006       7          5          CA060208006      220060207G723023059598        SCROLL          ALLSN                   HUGHES369   369D        4470706WP  ALLSN 250C  250C20B     03013GL                              ANTI ICE BOSS   CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            1480  CAC33937                                            (CAN) ON INSPECTION THE ENGINEER WAS TAKING APART THE ANTI-ICE BODY 6856984 FOR INSPECTION AND FOUND A CRACK AROUND THE BOSS. (TC NR 20060208006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1G71 3U3  U  H3WE    E4CE                 
20060705002442006070500244WP  2006       7          5          CA060208007      120060207G6730D2121           SERVO                                   ROBSINR44   R44         7640120WP  LYC   O540  O540F1B5    41532EA                              ROTOR           LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA            455                                                       (CAN) DURING AN INSPECTION HYDRAULIC LEAKS WAS FOUND AROUND THE FWD AND AFT SERVOS.THE RT FWD SERVO S/N 0251 AND THE AFT SERVO S/N 0667 WERE REMOVED AND NEWLY OVERHAULED ARE BEING INSTALLED. (TC NR 20060208007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1G71 3O3  O  H11NM   E295                 
20060705002462006070500246NM  2006       7          5          CA060208009      120060207G2910NAS1611130      O-RING                                  BOEING727   727247      138408FNM  PWA   JT8   JT8D15      52051NE                              HYD SYSTEM      SWOLLEN         W      A   UNSCHED LANDING                                                                                 K  FLUID LOSS                                                                    CLCLIMB          1                      CA       7336                                                           (CAN) SHORTLY AFTER TAKEOFF, CREW NOTICED SYS (A) HYDR INDICATED ZERO QTY. CREW DECLARED AN EMERGENCY, ASKED FOR A RETURN TO AIRPORT. CREW REQUESTED A FUEL DUMP, THIS WAS APPROVED BY ATC. AFTER FUEL DUMPING WAS COMPLETED AC RETURNED AIRPORT FOR ARRIVALS ILS 29. AC LANDED SAFELY AND WAS TOWED TO RAMP. INSP WAS ACCOMPLISHED. CAUSE OF HYDR FAILURE WAS  FAILED O-RING EXTRUDING FROM IB FLAP PWR UNIT HYDR MOTOR. MOTOR ASSY AND O-RING REPLACED, (A) SYSTEM FILTERS REMOVED, INSPECTED FOR METAL. FILTERS FOUND CLEAN. OB MOTOR WAS REMOVED, INSPECTED, FOUND SERVICEABLE.  IAW MM FILTERS TO BE REINSPECTED AFTER 200 HOURS.  AC HYDR SYS SERVICED, AC WAS RETURNED TO SERVICE. (TC NR 20060208009)                                   2L73 4F4  F  A3WE    E2EA                 
20060705002852006070500285EA  2006       7          5          CA060208011      220060202G732125244392        FCU                                     DHAV  DHC6  DHC6200     2802620EA  PWA   PT6   PT6A20      52043EA  HARTZLHCB3T HCB3TN3     GL  ENGINE          FLUCTUATES      W      A   UNSCHED LANDING                                                                                 XMJENGINE FLAMEOUT           OVER TEMP                 WARNING INDICATION        DEDESCENT        1                      CA            3479                                                      (CAN) WHEN AC WAS ABOUT 10 MIN FROM LANDING, ON DESCENT, ENG POWER LEVERS WERE RETARDED FROM 38 LBS OF TORQUE. THE RT ENGINE TQ AND T5 STARTED FLUCTUATING. RT POWER LEVER WAS BROUGHT BACK FURTHER BUT TQ AND T5 CONTINUED TO RISE. RT POWER LEVER WAS PUT TO IDLE AND PROP LEVER TO FULL FINE IN AN ATTEMPT TO REDUCE TQ AND T5 HOWEVER BOTH PARAMETERS STILL INCREASED FURTHER TO 55 LBS OF TQ AND 900 DEGREES ON T5. ENG WAS SHUT DOWN AND THE AC LANDED WITHOUT INCIDENT. FCU WAS REPLACED, RIGGED AND ENGINE RUN-UPS COMPLETED. AC WAS FLOWN BACK TO BASE. RT POWER SECTION WAS REMOVED AND SENT FOR AN OVER TORQUE INSPECTION, AND THE FCU SENT FOR REPAIR.   (TC NR 20060208011)                                                        1H72 3T3  TRTA9EA    E4EA    6  CP15EA    
20060711001512006071100151EA  2006       7          11         CA060208015      120060130G712073512562        MOUNT                                   DHAV  DHC6  DHC6300     2802606EA                                                               ENGINE          BROKEN          W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             CRCRUISE         1                      CA       631                                                            (CAN) THE PILOT REPORTED AFTER LANDING THE LT ENGINE WAS BROKEN. THE MAINTENANCE CREW REPLACED THE BROKEN TOP LT ENGINE MOUNT ALONG WITH THE VIBRATION ISOLATOR AND NEW GASKETS AND ATTACHMENT BOLTS. (TC NR 20060208015)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H72 3T    RTA9EA                         
20060711001522006071100152CE  2006       7          11         CA060209001      120060131G2910CM3574D460B0    HOSE                                    CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              HYD SYSTEM      BURST           W      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  LDLANDING        1                      CA       6000                                                           (CAN) LANDING THE CREW DEPLOYED THE THRUST REVERSERS AND GOT 6 LIGHTS FOLLOWED BY (HYD LOW LEVEL) AND (HYD LOW FLOW) LIGHTS. MAINTENANCE FOUND ONE LINE P/N CM3574D460B000S ON THE LT SIDE HAD BURST. REPLACED LINE WITH NEW. INSPECTED BOTH PRESSURE FILTERS AND NO METAL WAS FOUND. THE HYDRAULIC RESERVOIR WAS SERVICED AND THE THRUST REVERSER AND SPEED BRAKES WERE FUNCTION CHECKED. STARTED RT ENGINE TO PERFORM FUNCTION CHECKS. INSPECTED HYDRAULIC FILTERS FOR METAL, NONE FOUND. AIRCRAFT PLACED ON JACKS AND GEAR SWING COMPLETED. AIRCRAFT RETURNED TO SERVICE. (TC NR 20060209001)                                                                                                                                                1L72 4F4  F  A22CE   E1NE                 
20060711001532006071100153WP  2006       7          11         CA060209002      120060207G3222MS288891        PRESSURE VALVE                          NAMER B25   B25J        6400710WP  WRIGHTR2600 R260035     67050EA  HAMSTD23E   23E50       NE  NLG             INOPERATIVE     W      O   OTHER                                                                                           J  WARNING INDICATION                                                            CLCLIMB          1                      CA       4534                                                           (CAN) AC NOSE WHEEL STEERING INDICATOR SHOWED A NON-CENTRED CONDITION OF NOSE WHEEL IMMEDIATELY AFTER TAKE-OFF.  AFTER SEVERAL LOW FLYOVERS TO VISUALLY CHECK CONDITION,  EMERGENCY WAS DECLARED, AC WAS LANDED.  POST LANDING, NOSE OLEO WAS DISCOVERED TO HAVE BECOME FULLY DEFLATED (ALTHOUGH THERE WAS NO OIL LEAKAGE), WHICH PREVENTED  OLEO FROM FULLY EXTENDING, THUS NOT ALLOWING INTERNAL CENTERING DEVICE TO CENTER THE WHEEL.  SOURCE OF LEAK WAS DETERMINED TO BE A LEAKING HIGH PRESSURE INFLATION VALVE (SCHRADER).  WHILE VALVE IS CORRECT ONE, CALLED FOR IN PARTS MANUAL, STANDARD PRACTICE TO INSTALL MECHANICALLY CLOSED VALVES. THIS WAS DONE, OPERATION OF OLEO CENTRING DEVICE WAS CONFIRMED. (TC NR 20060209002)         2M72 4R4  R  AL2     PAGE42  6  CP603     
20060711001542006071100154    2006       7          11         CA060209003      420060202G6122                GOVERNOR                                CESSNA172   R172K       2072431CE  CONT  O360  IO360KB     17025SO  MCAULY2A34C 2A34C203    GL  PROPELLER       DAMAGED         W      O   OTHER                                                                                           E  VIBRATION/BUFFET                                                              CLCLIMB          1                      CA       2295 477                           356706                      (CAN) ENGINE OVERSPEED ON A TOUCH AND GO LANDING AT AIRPORT, ON TAKEOFF. ENGINE WAS REPORTED ROUGH ON THE RETURN FLIGHT.  THE INSTRUCTOR AND THE OWNER ONBOARD DECIDED TO DECLARE AN EMERGENCY AND LAND BACK WHERE THE AIRCRAFT IS BASED AT THIS TIME.  MAINTENANCE HAS DISCOVERED THAT THE SPARK PLUGS WHERE FOULED AND IN POOR SHAPE THE PROP GOVENOR WAS REMOVED FOUND BITS OF A RUBBER SEAL OR O-RING MATERIAL. GOVERNOR WAS SENT OUT FOR TESTING AND RECERTIFICATION. THIS WORK WAS ACCOMPLISHED ON FEB 8 2006. (TC NR 20060209003)                                                                                                                                                                                                        1H71 3O3  O  3A17    E1CE    5  CP3EA     
20060711001552006071100155SW  2006       7          11         CA060209004      120060206G5524214001920101    HORN                                    BELL  214   214B1       1182105SW  LYC   T55   T5508D      41555NE                              ELEVATOR        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       551                                                            (CAN) AFTER LANDING AND SHUTDOWN, DURING REGULAR INSPECTION, A CRACK WAS FOUND IN THE ELEVATOR HORN ASSY. PART WAS REMOVED AND REPLACED BEFORE FURTHER FLIGHT. (UNDER CODES F1 WAS USED HOWEVER FLIGHT CONTROLS WERE NOT AFFECTED, AS  PILOT DID NOT NOTICE ANY CHANGE IN FLIGHT CARACTERISTICS. THE ELEVATOR WAS STILL ABLE TO FUNCTION NORMALY WITH THE CRACK. (TC NR B20060209004)                                                                                                                                                                                                                                                                                                                                                           2G71 4U4  U  H6SW    E4NE                 
20060711001562006071100156EU  2006       7          11         CA060209005      120060207G243523079009        STARTER GEN                             BAG   JETSTMJETSTM3212  1500217EU  GARRTTTPE331TPE33110UG  01514WP  MCAULY4HFR344HFR34C652  NE  RT              FAILED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            APAPPROACH       1                      CA            1132                                                      (CAN) RT GENERATOR FAILER INDICATION ON APPROACH. CREW LANDED A/C WITH NO MORE PROBLEMS.  STARTER/GENERATOR REPLACED. STARTER/GEN 67.9 HOURS REMAINING BEFORE OVERHAUL DUE. BRUSH INSPECTED TO BE 20 PERCENT  REMAINING. (TC NR 20060209005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4T4  TRTBA15CAA E4WE    6  C3PNE     
20060711001572006071100157CE  2006       7          11         CA060209006      120060208G53120411951         BULKHEAD                                CESSNA150   150         2071802CE  CONT  O200  O200A       17020SO  MCAULY1A100 1A100*      GL  MLG WW          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING AN ANNUAL INSPECTION, AM AME NOTICED THE MLG STRUT BULKHEAD UNDER THE CABIN FLOOR HAD SMALL CRACKS. UPON FURTHER INSPECTION WITH THE FLOORS REMOVED IT WAS FOUND THE ENTIRE MLG ATTACHMENT BULKHEAD/BOX STRUCTURE WAS NEAR FAILURE. MANY COMPONENTS MAKE UP THE ENTIRE BOX STRUCTURE AND MANY OF THEM WERE CRACKED OR FAILED. ALL THE DAMAGED AND CRACKED COMPONENTS WERE REPLACED WITH NEW PARTS AND REASSEMBLED.  THE PN OF THE 2 BULKHEADS ARE 0411951-5 AND -6. (TC NR 20060209006)                                                                                                                                                                                                                                            1H71 3O3  ONT3A19    E252    5  NP918     
20060711001582006071100158EA  2006       7          11         CA060210001      120060209G5740C6WM102727      FITTING                                 DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A27      52043EA  HARTZLHCB3T HCB3TN3     GL  RT WING         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       32840                                                          (CAN) UPON INSPECTION OF WING FRONT SPAR ADAPTER FITTINGS IAW REO 6-57-30-013, CRACKS WERE FOUND ON THE LT AND RT WING FRONT SPAR ADAPTER FITTINGS AS FOLLOWS; LT WING, BETWEEN WING STATION 35.15 AND 47.5, ONE CRACK BETWEEN 5TH AND 6TH RIVET. LT WING, BETWEEN WING STATION 47.5 AND 60.0, ONE CRACK BETWEEN THE 7TH AND 8TH RIVET. RT WING BETWEEN WING STATION 35.15 AND 47.5, ONE CRACK BETWEEN 4TH AND 5TH RIVET. AIRCRAFT ADVISED. (TC NR 20060210001)                                                                                                                                                                                                                                                                                 1H72 3T4  TRTA9EA    E4EA    6  CP15EA    
20060710001032006071000103NM  2006       7          10         CA060210002      120060209G3297                GROUND WIRE                             BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                              MLG SELECTOR    LOOSE           W      O   OTHER                                                                                           O  OTHER                                                                         APAPPROACH       1                      CA                                                                      PILOT REPORTED THAT THE LANDING GEAR DID NOT EXTEND ON SELECTION.  AN ALTERNATE GEAR EXTENSION SELECTION WAS CARRIED OUT AND THE AIRCRAFT LANDED WITH OUT INCIDENT.  THE PSEU HISTORY AND PRESENT FAULT WERE AS FOLLOWS: "DIN 01A FAULT"(DISCRETE INPUT EXTEND COMMAND) THE PROBLEM WAS TRACED TO A LOOSE GROUND "GS9" CONNECTED TO THE  LANDING GEAR CONTROL AND INDICATION PANEL CONNECTOR P55  PIN "P".  REF: WDM 32-61-00  SHT 7 OF 12 PAGE 1.                                                                                                                                                                                                                                                                                              2H72 4T4  TRTA13NM   E00062EN             
20060711001642006071100164EU  2006       7          11         CA060210003      120060131G3010FAL1007         HOSE                                    AMD   FALC10FALCON10    2730101EU  GARRTTTFE731TFE7312     01518WP                              RT SLAT         COLLAPSED       W      O   OTHER                                                                                           J  WARNING INDICATION                                                            APAPPROACH       1                      CA       111  111                                                       (CAN) DURING APPROACH THE FLIGHT CREW NOTICED THAT THE RT OB SLAT WAS NOT SHEDDING ICE WITH THE WING ANTI-ICE ACTIVATED. UPON INSPECTION THE RT OB SLAT FLEX HOSE WAS FOUND TO BE SLIGHTLY COLAPSED INTERNALLY.  ANTI-ICE SYSTEM WAS ACTIVATED 44 TIMES.  (TC NR 20060210003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  F  A33EU   E6WE                 
20060711001932006071100193EU  2006       7          11         CA060210004      120060126G2822P94B12208       PUMP                                    SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1        NE                              LT FUEL BOOST   FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) BOOST PUMP JUST STOPPED WORKING. REMOVED AND INSTALLED OVERHAUL PUMP SAME P/N AND ALL IS OK. (TC NR 20060210004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1G71 3U3  U  H9EU    E19EU                
20060711001942006071100194WP  2006       7          11         CA060210006      120060202G2822B8187B          PUMP                                    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              FUEL SYS        NOISY           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       882                                                            (CAN) PILOT RECORDED A DEFECT THAT THE PUMP WAS MAKING A GRINDING NOISE.  PUMP ASSEMBLY WAS REPLACED.  NO FURTHER DEFECTS NOTED. (TC NR 20060210006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1G71 3O3  O  H11NM   1E4                  
20060808001012006080800101NE  2006       8          8          CA060210007      220060203G7200                ENGINE                                  SKRSKYS92   S92A               NE  GE    CT7TP CT79B       30030NE                              NR 2            MAKING METAL    W      O   OTHER                                                                                           J  WARNING INDICATION                                                            CRCRUISE         1                      CA       42                                                             (CAN) AFTER TAKE-OFF, ENGINE NR 2 CHIP LIGHT STARTED TO FLICKER.  AC WAS TURNED AROUND TOWARDS PLACE OF DEPARTURE. EMERGENCY CHECKLIST WAS FOLLOWED, ENG NR 2 WAS BROUGHT BACK TO IDLE.  DURING A LONG FINAL ON DESCENT, ENGINE WAS BROUGHT BACK ON LINE FOR LANDING.   AC LANDED WITHOUT FURTHER INCIDENT, RETURNED TO HANGAR FOR INSP. AFTER INVESTIGATION,  TECH REPS WERE CONTACTED, RECOMMENDED A GROUND RUN AS OUTLINED IN MM. THIS GROUND RUN WAS CARRIED OUT, THERE WAS NO CHIP LIGHT BUT UPON FURTHER INVESTIGATION SOME METAL CONTAMINATION WAS FOUND ON THE CHIP PLUG, IT WAS UPON THE ADVICE OF THE MANUFACTURER TO REPLACE THE ENGINE. THE ENGINE WAS REPLACED AND THE A/C WAS RETURNED TO SERVICE.                                2G72 4U4  T  R00024BOE8NE                 
20060711001952006071100195CE  2006       7          11         CA060210008      120060209G7110                LATCH                                   BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA                              RT COWL         LOOSE           W      A   UNSCHED LANDING                                                                                 D  INFLIGHT SEPARATION                                                           CRCRUISE         1                      CA       9741                                                           (CAN) RT ENGINE COWLING UNLATCHED IN FLIGHT (CALLED IN PRIORITY LANDING). RT ENGINE COWLING INSPECTED, FOUND FORWARD LATCH WAS LOOSE. RT ENGINE COWLING SECURED. RETRAINING CARRIED OUT WITH FLIGHT CREW AND TECHNICIANS ON PROPER COWLING LATCHING PROCEDURES.  (TC NR 20060210008)                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L72 4T4  T  A24CE   E4EA                 
20060711001962006071100196NM  2006       7          11         CA060210009      120060210G531285310109        ANGLE                                   DHAV  DHC8  DHC8102     2809003NM                                                               BULKHEAD        CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       35538                                                          (CAN) DURING A C-CHECK HEAVY CORROSION WAS FOUND ON THE FRONT PRESSURE BLK STA 120.0 ON THE LOWER AFT CAP ANGLE P/N 85310109 AND ON THE FORWARD CAP ANGLE P/N 85310108. THE DAMAGE WAS SUBMITTED TO MFG WHO ISSUE A SPECIFIC REPAIR TO BE CARRIED OUT. (TC NR 20060210009)                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2H72 4T    RTA13NM                        
20060711001972006071100197    2006       7          11         CA060211001      420060210G6113                PLATE                                   DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE  HARTZLHCB3R HCB3R304    GL  PROPELLER       DAMAGED         W      O   OTHER                                                                                           W  INADEQUATE Q C                                                                TXTAXI/GRND HDL  1                      CA       89                                                             (CAN) SHEARED RIVETS ON BACKPLATE FACE. (TC NR 20060211001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1H71 3R3  RRCA806    5E1     5  CP28EA    
20060711001982006071100198EA  2006       7          11         CA060211002      120060207G5610NP1393226       WINDOW                                  CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30015NE                              COCKPIT         CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         DEDESCENT        1                      CA                                                                      (CAN) THE COPILOT SIDEWINDOW CRACKED IN DESCENT.  WINDOW REPLACED, AIRCRAFT RELEASED TO SERVICE.  (TC NR 20060211002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F4  FRTA21EA   E15NE                
20060711002012006071100201NM  2006       7          11         CA060213001      120060212G7921800600M03005    ACTUATOR                                BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  NR 2 NACELLE    OVERHEATED      W      A   UNSCHED LANDING                                                                                 M  OVER TEMP                                                                     CRCRUISE         1                      CA                                                                      (CAN) ABOUT TEN MINUTES AFTER TAKEOFF NR 2 ENGINE OIL TEMPERATURE STARTED RISING, CREW WENT THROUGH CHECKLIST CLOSED BYPASS DOORS, TEMPERATURE WAS ABOVE 107 DEGREES FOR ABOUT 20 MINUTES AND ABOVE 115 DEGREES FOR ABOUT 10 MINUTES. TEMPERATURE PEAKED AT 122 DEGREES THEN IT STARTED COOLING AGAIN ON OUR DESCENT BACK TO BASE.  BY THE TIME THE CREW LANDED, THE TEMPERATURE WAS NORMAL AT 94 DEGREES. OIL COOLER DOOR ACTUATOR WAS DETERMINED TO BE THE CAUSE. THE OIL COOLER DOOR ACTUATOR REPLACED. (TC NR 20060213001)                                                                                                                                                                                                                  2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
20060719000322006071900032SW  2006       7          19         CA060213002      120060212G2140ES721822        AIR DUCT        AIRCOM                  BELL  206   206B        1181511SW  ALLSN 250C  250C20      03013GL                              CABIN HEATER    MELTED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING MAINTENANCE, AN AME NOTICED THAT HE COULD NOT MOVE THE HEATER AIR OUTLET.  ON CLOSER INVESTIGATION, HE FOUND THE OUTLET MELTED.  NO OTHER DAMAGE WAS NOTED. (TC NR 20060213002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1G71 3U3  U  H2SW    E4CE                 
20060719000332006071900033NM  2006       7          19         CA060213003      120060210G275118157014        TRANSMITTER                             BOEING727   727247      138408FNM  PWA   JT8   JT8D15      52051NE                              IB TE FLAP      FAILED          W      L   ABORTED APPROACH                                                                                FJ FLT CONT AFFECTED         WARNING INDICATION                                  APAPPROACH       1                      CA       7591                                                           (CAN) AIRCRAFT EXPERIENCED A FLAP ASYMMETRY ON APPROACH. CREW DECLARED AN EMERGENCY AND ELECTRICLY DROVE THRU FLAPS TO LANDING CONFIGURATION. AIRCRAFT LANDED SAFELY AND WAS TAXIED TO THE HANGER. HANGER MAINTENANCE CONFIRMED THE LT IB FLAP TRANSMITTER AS THE CAUSE. LT IB FLAP TRANSMITER REPLACED AND ENTIRE FLAP SYSTEM CHECKED FOR RIGGING IAW THE MM. NO FURTHER FAULTS FOUND. SUBMITTER WILL UP-DATE THIS SDR AS MORE INFORMATION COMES IN FROM FLIGHT CREW. (TC NR 20060213003)                                                                                                                                                                                                                                                      2L73 4F4  F  A3WE    E2EA                 
20060719000342006071900034EA  2006       7          19         CA060213004      120060210G2910MM67075294009   LINE                                    CNDAIRCL215 CL2151A10   1900320EA  GE    CF34  CF348C1          NE                              NR 2 HYD SYS    CRACKED         W      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) TOTAL LOSS OF NR 2 HYDRAULIC FLUID, FROM A RUPTURE ON THE PRESSURE MANIFOLD LINE P/N MM670-75294-009. NR 2 HYDRAULIC LINES P/N MM670-75294-009, MM670-75294-005 AND SUPPORT CLAMPS P/N MM670-75800-041, MM670-75800-029 ALL REPLACED. ENGINE DRIVEN PUMP FAILED AND REPLACED. IT IS SUSPECTED THE CAVITATIONS CAUSED BY THE FAILURE OF THE ENGINE DRIVEN PUMP CAUSED EXCESSIVE BUFFETING IN THE HYDRAULIC LINES. THE BUFFETING OF THESE LINES CAUSED DAMAGE TO THE CLAMPS AND RESULTED IN THE HYDRAULIC LINE CHAFING THROUGH UNTIL TOTAL LOSS OF HYDRAULIC FLUID OCCURED. (TC NR 20060213004)                                                                                                                                             2H72 4R4  FRTA14EA   EOOO63EN             
20060719000362006071900036NE  2006       7          19         CA060213006      220060209G7510577957          MANIFOLD                                BOEING727   727227      1384078NM  PWA   JT8   JT8D9A      52048NE                              ENGINE          CRACKED         W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) AFTER DEPARTURE, THE NR 2 FIRE WARNING CAME ON THROUGH CLIMB, POWER LEVER REDUCED WITH SUBSEQUENT WARNING EXTINGUISHING AND AIRCRAFT RETURNED.  INSPECTION CARRIED OUT AND FOUND THE NR 2, 13TH STAGE FUEL HEAT DUCT RUPTURED AT BOTH ENDS. THE DUCT WAS THEN REPLACED.  (TC NR 20060213006)                                                                                                                                                                                                                                                                                                                                                                                                                                              2L73 4F4  F  A3WE    E2EA                 
20060719000372006071900037SW  2006       7          19         CA060213008      120060210G5302206033004051    SKIN            BELL                    BELL  206   206L        1181522SW                                                               TAILBOOM        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                  AORP00728                                           (CAN) DURING A 100 HOUR INSPECTION THE ENGINEER DISCOVERED 2 CRACKS EMINATING FROM 2 RIVETS ON THE THE TAIL ROTOR GEARBOX ATTACH SUPPORT.  THE CRACKS GO OUT TO THE EDGE OF THE SKIN.  THE RIVETS WERE ALSO FOUND TO BE SMOKING OR LOOSE. (TC NR 20060213008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1G71 3U      H2SW                         
20060719000382006071900038CE  2006       7          19         CA060214001      120060213G2133NN5040          TUBE                        10357626    CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              OUTFLOW VALVE   MELTED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING UNSCHEDULED MAINT FOR AN UNRELATED MAINTENANCE ISSUE, THE POLYFLOW LINE PROVIDING ATMOSPHERIC REFERENCE PRESSURE TO THE RT OUTFLOW VALVE WAS FOUND MELTED AND OPEN TO CABIN PRESSURE. THE POLYFLOW LINE WAS TOO LONG AND WAS POSITIONED IN SUCH A WAY AS TO REST AGAINST THE EMERGENCY PRESSURIZATION LINE P/N: 6515201-3. THE HEAT FROM THE EMERGENCY PRESSURIZATION LINE CAUSED NYLON TUBING TO MELT.  NEW TUBING OF THE CORRECT LENGTH WAS INSTALLED AND ROUTED CLEAR OF THE EMERGENCY PRESSURIZATION LINE. AIRCRAFT WAS RETURNED TO SERVICE.  AC SERVICES HAS INITIATED CAMPAIGN 851-21-30-031TO INSPECT THE REST OF OUR FLEET FOR CORRECT INSTALLLATION OF THE POLYFLOW LINE. (TC NR 20060214001)                             1L72 4F4  F  A22CE   E1NE                 
20060719000392006071900039EU  2006       7          19         CA060214002      120060214G783028850009        LOCK                                    AIRBUSA340  A340313            EU  CFMINTCFM56 CFM565C4    13802NE                              THRUST REVERSER MALFUNCTIONED   W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) THRUST REVERSER NR 4 UNLOCKED. SHUTDOWN NR4 V/S ON OVERWEIGHT LANDING 500FT/MIN LANDING WT 233000 KG.   SEE FMR M1243972. ACTION:411T/S 78-31-00-810-970 CARRIED OUT NO FAULT FOUND.  SUSPECT PRIMARY LOCK P/N 2885000-9 LOCATED AT IB UPPER SIDE. 4 LOCK PLUGS ARE LOCATED IN THE OB PARTS BOX. (TC NR 20060214002)                                                                                                                                                                                                                                                                                                                                                                                                                      2L74 4F4  FRTA197    E37NE                
20060719000402006071900040EU  2006       7          19         CA060214003      120060207G2710LN93614C46R210  CONTROL CABLE                           CASA  C212  C212CC      2410204EU  GARRTTTPE331TPE33110R   0517 WP  HARTZLHCB4M HCB4M       GL  AILERONS        BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       18632                                                          (CAN) DURING ROUTINE MAINTAENANCE INSPECTION, SEVERAL WIRES FOUND BROKEN ON RT AILERON CONTROL CABLE AS IT PASSES AROUND CABLE PULLEY AT FRAME 4. PULLEY FOUND SEIZED TO BOLT. CABLE, PULLEY AND BOLTS REPLACED. (TC NR 20060214003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2H72 4T4  T  A43EU   E4WE    6  CP56GL    
20060719000652006071900065NM  2006       7          19         CA060214004      120060214G3244314381          TIRE                                    BOEING737   737522      138449FNM  CFMINTCFM56 CFM563C1    13802EU                              NOSE GEAR ASSY  DEFLATED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) WHEN MAINTENANCE ARRIVED AT THE GATE FOR THE DAY'S FIRST DEPARTURE, IT WAS NOTICED THAT THE LT NOSE TIRE WAS FLAT. UPON FURTHER INVESTIGATION IT WAS DISCOVERED THAT THE RT NOSE TIRE WAS ALSO FLAT. BOTH NOSE ASSEMBLIES REPLACED AND AIRCRAFT RETURNED TO SERVICE.  (TC NR 20060214004)                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA16WE   E21EU                
20060719000662006071900066SO  2006       7          19         CA060214005      120060213G2121C180559A1       BLOWER                                  EMB   110   EMB110P1    3260122SO  PWA   PT6   PT6A34      52043EA  HARTZLHCB3T HCB3TN3     GL  CABIN AIR       BURNED          W      A   UNSCHED LANDING                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA       1598 447                                                       (CAN) DURING CRUISE FLIGHT, WITH NO PASSENGERS ON BOARD, THE CREW NOTICED AN ELECTRICAL BURNING SMELL IN THE AIRCRAFT AND SMOKE IN THE CABIN. THE AIRCRAFT WAS DIVERTED TO THE NEAREST SUITABLE AIRPORT AND LANDED. UPON INVESTIGATION MAINTENANCE PERSONNEL DISCOVERED THAT THE SMELL AND SMOKE WAS COMING FROM THE CABIN BLOWER. THE CABIN BLOWER WAS DISABLED AND DEFERRED AND A GROUND RUN WAS COMPLETED WITH NO FURTHER SMOKE OR BURNING SMELL NOTED. THE AIRCRAFT WAS THEN RETURNED TO SERVICE. ONCE THE AIRCRAFT RETURNED TO A MAINTENANCE BASE THE BLOWER WAS REMOVED AND SENT OUT FOR REPAIR AND A COMPONENT STRIP REPORT. (TC NR 20060214005)                                                                                         1L72 4T4  T  A21SO   E4EA    6  CP15EA    
20060719000672006071900067GL  2006       7          19         CA060214006      220060210G72606820588         WASHER          ALLSN                   AEROSPAS355 AS355*             EU  ALLSN 250C  250C20R1    03013GL                              GEARBOX         MISSING         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                  CAG40968                                            (CAN) AS ENG NR 2 WAS INCREASED, EXCEEDANCE ON INSTR PANEL, M/R READING HIGH ON TRIPLE TACH, NO INDICATION OF N2 SPEED ON TACH INDICATOR. FOUND N2 GOV GEAR FREEWHEELING, DISENGAGED FROM INTERNAL GB N2 DRV SYS.   TEARDOWN OF GB REVEALED BRG RETAINING WASHER WAS MISSING, N2 PWR TRAIN IDLER GEAR ASSY.  WASHER RETAINS BRG ON IDLER GEAR SUPT SHAFT. KEY WASHER RETAINED BRG ON IDLER SUPT SHAFT, UNTIL BRG INNER RACE WORE EDGE OF KEY WASHER ALLOWING BRG TO SLIDE AXIALLY, DISENGAGE N2 TACH DRV GEARTRAIN. WITH N2 TACH DRV GEARTRAIN DISENGAGED FROM N2 DRV, ENG COULD OVERSPEED.  WEAR ON ID OF N2 PWR TRAIN IDLER BRG, PORTION OF KEY WASHER, IDLER GEAR. PREVIOUS CHIP LIGHTS REPORTED ARE RESULT OF WEAR. (TC NR 20060214006)     1G72 3U3  U  H11EU   E4CE                 
20060719000682006071900068NM  2006       7          19         CA060214007      120060210G2730BACB10ET06      BEARING                                 BOEING757   757*               NM  RROYCERB211 RB211535E43754555NE                              ELEVATOR        SEIZED          W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             CLCLIMB          1                      CA       52087                                                          (CAN) REPORTED THAT ELEVATOR FELT HEAVY FOR BOTH CAPT AND F/O. AILERON NORMAL.  TROUBLESHOOTING SHOWED THAT THE ROLLER BEARING THAT RIDES IN THE ELEVATOR INPUT CAM WAS SEIZED, CAUSING HIGHER THAN NORMAL FORCE REQUIED TO MOVE FLIGHT CONTROL OUT OF (DETENT).  BEARING REPLACED AND SYSTEM CHECKED IAW AMM 27-31-17 P216, OPS FOUND NORMAL.   AFTER BEARING REPLACEMENT, NO FURTHER DEFECTS NOTED. (TC NR 20060214007)                                                                                                                                                                                                                                                                                                                       2L72 4F4  FRTA2NM    E12EU                
20060719000692006071900069CE  2006       7          19         CA060215001      120060213G3411AERROQUIP206    HOSE                                    LEAR  35    35LEAR      5170600CE  GARRTTTFE731TFE73122B   01518WP                              PITOT SYS       CRACKED         W      K   NONE                                                                                            L  NO TEST                                                                       ININSP/MAINT     1                      CA       1873                                                           (CAN) DURING A SCHEDULED PITOT/STATIC CHECK, THE AVIONICS TECHNICIAN DISCOVERED A LEAK ON THE LT PITOT CIRCUIT.  AFTER FURTHER TROUBLESHOOTING, THE TECHNICIAN DISCOVERED A HOSE THAT WAS CRACKED (MIL-H-5593-4).  THE HOSE WAS REPLACED AND THE SYSTEM WAS SERVICEABLE. (TC NR 20060215001)                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F4  F  A10CE   E6WE                 
20060719000702006071900070GL  2006       7          19         CA060215002      220060213G72616870032N        FILTER                                                                     ALLSN 250C  250C20      03013GL                              OIL SYSTEM      DAMAGED         W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA                                                                      (CAN) ENGINE OIL FILTER, VENDOR NR IS 05228-759280-101.  THERE WAS A PROBLEM WITH ONE OF THE SEAMS IN ONE OF THE ELEMENTS NOT BEING SEALED.  ALL OF THE PTI FILTERS IN STOCK WERE INSPECTED AND FOUND THE SAME DEFECT IN EACH FILTER.  THE FILTERS WERE PURCHASED AND THE VENDOR HAS BEEN NOTIFIED OF THIS DEFECT AND ALL THE FILTERS HAVE BEEN PLACED IN QUARANTINE STORES PENDING RETURN TO THE VENDOR. (TC NR 20060215002)                                                                                                                                                                                                                                                                                                                          3  U          E4CE                 
20060719000712006071900071EA  2006       7          19         CA060215003      220060210G72603027977         CARRIER ASSY                                                               PWA   PT6   PT6A6       52043EA                              RGB             DISPLACED       W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2998 16                                                        (CAN) OPERATOR COMPLAINED OF NOISE FROM THE REDUCTION GEARBOX, EXCESSIVE PROPELLER LOOSENESS AND METAL ON THE RGB CHIP DETECTOR. UPON GEARBOX DISMANTLE AND EXAMINATION OF THE 2ND STAGE CARRIER (PN 3027977), THE SLEEVE USED TO REPAIR THE NR 5 BEARING JOURNAL WAS FOUND TO HAVE SHIFTED OFF OF THE JOURNAL (REFER TO FIGURES 1 AND 2).  NO SECONDARY DAMAGE TO THE REDUCTION GEARBOX ASSEMBLY WAS NOTED.   THE SLEEVE REPAIR IS PERMITTED ON 2ND STAGE CARRIER PN 3027977 FOR OTHER ENGINE MODELS, AND THIS PART NR IS ELIGIBLE FOR USE ON THE ENGINE, HOWEVER SLEEVE REPAIR IS PROHIBITED IAW MM 3034543 FOR THE ENGINE APPLICATION.  (TC NR 20060215003)                                                                                         3  T          E4EA                 
20060719000722006071900072EA  2006       7          19         CA060216001      120060215G243503600923        BEARING         BFGOODRICH              DHAV  DHC8  DHC8311     1386006EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF15      NE  STARTER GEN     FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       189971231  Y20071R                                             (CAN) ORIG SNAG (STARTER SWITCH DOES NOT AUTO DELATCH) DRIVE END BEARING FAILURE (03-6009-23)  STARTER GENERATOR HAS BEEN MODIFIED TO -008 (S/B -8-24-81)   (TC NR 20060216001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060719000732006071900073EU  2006       7          19         CA060216002      120060124G6321AHA1121         CALIPER                                 BOLKMS105   BO105C      5626005EU  ALLSN 250C  250C20B     03013GL                              MAIN ROTOR BRAKEBINDING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) PISTON DOES NOT RETRACT INTO CALIPER HOUSING AFTER BRAKING CAUSING ROTOR BRAKE PAD TO REMAIN IN CONTACT WITH BRAKE DISC.  (TC NR 20060216002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1G72 3U3  U  H3EU    E4CE                 
20060616001282006061600128CE  2006       6          16         CA060216003      120060215G5711                FRAME                                   BEECH 90    C90         1152913CE  PWA   PT6   PT6A28           EA  HARTZLHCB3T HCB3TN3     GL  WING            CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       16976                                                          UPON BEGINNING A PHASE 3 INSPECTION, A TECHNICIAN DISCOVERED A SMALL CRACK ON THE RIGHT FORWARD LOWER SPAR HINGE CAP.  THE CRACK WAS OUT FROM THE FOURTH FASTENER FORWARD TOWARD THE HINGE EDGE.  A SMALL AREA OF PAINT HAD BEEN FLAKED AWAY IN THIS AREA.  MORE PAINT WAS REMOVED IN THIS AREA IN AID TO FURTHER INVESTIGATE THE DISCREPANCY.  IT WAS CLEARLY VISIBLE TO SEE WITHOUT ANY NDT INSPECTION METHODS REQUIRED.  THE AIRCRAFT WAS REMOVED FROM SERVICE.  IT WAS NOTED THE PREVIOUS EDDY CURRENT INSPECTION (AS REQUIRED IAW THE RAYTHEON SIRM) WAS CONDUCTED IN THIS AREA IN JANUARY 2005, 754.8 HOURS AGO.                                                                                                                          1L72 3T4  T  3A20    E4EA    6  CP15EA    
20060606002252006060600225NM  2006       6          6          CA060216004      120060216G2140RBGB161         BLOCK                                   BOEING737   7378Q8      13844BXNM                                                               TERMINAL BLOCK  OVERHEATED      W      H   DEACTIVATE SYST/CIRCUITS                                                                        O  OTHER                                                                         ININSP/MAINT     1                      CA       1844518445                                                     REPLACING AFT WATER DRAIN MAST DUE TO INOPERATIVE HEATER.  GROUND TERMINAL BLOCK GD11996 WAS FOUND DAMAGED WITH SIGNS OF OVERHEATING.  WIRES DISCONNECTED AND CAPPED, AND EFFECTED CIRCUIT BREAKERS PULLED TO ISOLATE TERMINAL BLOCK UNTIL REPLACEMENT PART AVAILABLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA16WE                        
20060619001752006061900175NE  2006       6          19         CA060216005      220060215G74219550175400      IGNITER                                 SNIAS 350   AS350BA     8680817EU  TMECA ARRIELARRIEL1B    6OO30NE                              ENGINE          BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       547                                4374                        (CAN) DURING A 100 HR INSPECTION THE IGNITORS WERE REMOVED AND IT WAS FOUND THAT THE CERAMIC SURROUNDING CENTER ELECTRODE WAS LOOSE.  BOTH IGNITORS WERE CHAMPIONS.  ENGINE VIB CHECK WAS CARRIED OUT AND FOUND WITHIN LIMITS. LT IGNITOR S/N 04020731 AND RT S/N 03124329. (TC NR 20060216005)                                                                                                                                                                                                                                                                                                                                                                                                                                                 1G71 3U3  UNCH9EU    E19EU                
20060607002482006060700248NM  2006       6          7          CA060216006      120060216G28223823002         PUMP                                    BOEING727   727247      138408FNM  PWA   JT8   JT8D15      52051NE                              NR 2 FUEL TANK  UNKNOWN         W      A   UNSCHED LANDING                                                                                 GJ MULTIPLE FAILURE          WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      ON CLIMB, NR 2 RT AFT FUEL BOOST PUMP CB RELEASED FOLLOWED BY NR 2 LT AFT CB RELEASING APPROX 3 MIN LATER, NR 2 RT FWD CB RELEASED AND NR 2 LT FWD BOOST PUMP LOW PRESS LIGHT ILLUMINATED INTERMITTENTLY.  A/C RETURNED TO DEPARTURE.  MX INSPECTED ALL EFFECTED PUMPS, CONNECTORS, BREAKERS AND SWITCHES, NO FAULTS FOUND.  BREAKERS WERE RESET, PUMPS WERE RUN FOR AN HOUR.  DURING THIS TIME PUMPS WERE SELECTED OFF AND ON NUMEROUS TIMES.  A/C RETURNED TO SERV & OPERATED WITH NO INCIDENT.  MX REINSPECTED ALL OF ABOVE ALONG WITH CHECKING NR 2 TANK FOR FUEL CONTAMINATION.  NOTHING FOUND.  DUE TO UNUSUAL CIRCUMSTANCES MAINT HAS DECIDED TO REPLACE THREE EFFECTED BOOST PUMPS, BREAKERS AND SWITCHES.                              2L73 4F4  F  A3WE    E2EA                 
20060608001972006060800197CE  2006       6          8          CA060217001      120060214G315070H10A          DIODE                                   BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA                              COCKPIT         FAILED          W      O   OTHER                                                                                           GJ MULTIPLE FAILURE          WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA                  BB24                                                CREW REPORTS THAT MULTIPLE SYSTEMS AND ANNUNCIATORS UNSERVICEABLE.  MAINTENANCE PERSONAL DISPATCHED AND FOUND THAT NR 1 DUAL FED ELECTRICAL BUS HAD FAILED BOTH MAIN FEED DIODES (P/N 70H10A).  DIODES REPLACED AND FUNCTION CHECKED SERVICEABLE.  COMPANY HAS NOW IMPLEMENTED A MONTHLY REPETITIVE CHECK OF THE BUS SYSTEM DUE TO THE DORMANT FAILURE RISK OF THESE DIODES.                                                                                                                                                                                                                                                                                                                                                                    1L72 4T4  T  A24CE   E4EA                 
20060608003972006060800397CE  2006       6          8          CA060217002      120060207G323379990022A       ACTUATOR                                BEECH 100   A100        1152915CE  PWA   PT6   PT6A28           EA                              NLG             DAMAGED         W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      NOSE LANDING GEAR WOULD NOT RETRACT AFTER TAKEOFF.  MAINTEANCE DID MULTIPLE GEAR SWINGS BUT COULD NOT DUPLICATE THE PROBLEM.  THE ACTUATOR WAS REMOVED AND PUT IN A TEST STAND WHERE IT FINALLY FAILED STAYING IN THE LOCKED POSITION.  A OVERHAULED ACTUATOR WAS INSTALLED AND THERE HAS BEEN NO MORE PROBLEMS REPORTED.                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 3T4  T  A14CE   E4EA                 
20060607002512006060700251    2006       6          7          CA060217003      420060213G2562PS400010        ELT                                     ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540*      41532EA                              CABIN           ACTIVATED       W      K   NONE                                                                                            N  FALSE WARNING                                                                 CRCRUISE         1                      CA       194                                                            ELT ACTIVATED IN FLIGHT.  ELT REPLACED WITH SERVICEABLE UNIT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1G71 3O3  O  H11NM   1E4                  
20060608001992006060800199CE  2006       6          8          CA060218001      120060214G3230571302          MOTOR                                   BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE  HARTZLHCE4A HCE4A3I     NE  MLG             BURNED          W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      AFTER TAKEOFF, AIRCRAFTS LANDING GEAR WOULD NOT RETRACT.  CREW CONTACTED MX AND CREW AND MX DECIDED TO LEAVE THE LANDING GEAR DOWN AND CONTINUE THE 30 MINUTE FLIGHT TO THE MAIN BASE.  ALL INDICATIONS SHOWED THAT THE LANDING GEAR WAS DOWN AND LOCKED.  THE AIRCRAFT LANDED AND DEPLANED THE PASSENGERS AND RETURNED TO THE HANGAR.  WHEN MAINTENANCE TROUBLESHOT THE LANDING GEAR SYSTEM THE FAULT WAS FOUND WITH THE MOTOR.  MOTOR WAS REPLACED AND GEAR SWINGS CARRIED OUT SATISFACTORY.  THE PCB WAS ALSO REPLACED DUE TO THE TIME DELAY BUT THIS HAD NOTHING TO DO WITH THIS FAULT.  AIRCRAFT THEN RETURNED TO SERVICE.                                                                                                                 2L72 4T4  TRTA24CE   E26NE   5  CP10NE    
20060608002012006060800201CE  2006       6          8          CA060219001      120060117G55201158100714      SEAL                                    BEECH 100   100BEECH    1152916CE  PWA   PT6   PT6A28           EA                              TORQUE SHAFT    CUT             W      O   OTHER                                                                                           J  WARNING INDICATION                                                            NRNOT REPORTED   1                      CA                                                                      RUBBER SEAL DETERIORATED ALLOWING METAL SPRING TO CUT A LARGE GROOVE IN THE TORQUE SHAFT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 3T4  T  A14CE   E4EA                 
20060608002832006060800283EU  2006       6          8          CA060220001      120060214G3897E0266QF20EO261  WIRE HARNESS                            AIRBUS310   A310               EU  GE    CF6   CF680C2*         GL                              TOILET          BURNED          W      K   NONE                                                                                            S  AFFECT SYSTEMS                                                                ININSP/MAINT     1                      CA                                                                      AIRCRAFT ARRIVED AT STATION WITH A DEFECT LOG REPORT OF THE FORWARD LAVATORY NOT FLUSHING.  TROUBLESHOOTING FOUND THAT 4 WIRES BETWEEN THE FLUSH MOTOR AND THE TIMER UNIT WERE BROKEN.  IT WAS NOTED THAT MINOR ARCH/BURNING OF THE WIRES HAD OCCURRED.  ALL 4 WIRES AND PINS WERE REPLACED AND SYSTEM WAS TESTED SERVICEABLE.                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F4  FRTA35EU   E23EA                
20060612003542006061200354NM  2006       6          12         CA060220002      120060216G5330737200C         SKIN                                    BOEING737   737242C     1384478NM  PWA   JT8   JT8D9A      52048NE                              FUSELAGE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       71011                                                          DURING THE PREFLIGHT INSPECTION 2 CRACKS WERE OBSERVED IN THE FUSELAGE SKIN.  BOTH DEFECTS WERE APPROXIMATELY 2 INCHES IN LENGTH.  THE LOCATION IS ESTIMATED TO BE BS 750 STR 19/20.  THE AIRCRAFT IS CURRENTLY OUT OF SERVICE FOR REPAIR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F4  F  A16WE   E2EA                 
20060613000042006061300004    2006       6          13         CA060220003      120060216G4900MDL15R2001      SCREEN          BOMBDR                                                                                                                  APU INLET       DAMAGED         W      O   OTHER                                                                                           C  F.O.D.                                                                        NRNOT REPORTED   1                      CA                                                                      A COMPRESSOR INLET SCREEN MODIFICATION, AWI RECEIVED INFORMATION FROM STANDARD AERO LATE ON FEB 16,2006 THAT THREE OR FOUR OF THE SCREENS HAD RUPTURED IN SERVICE AND THERE WAS A POSSIBILITY THAT FOD TO THE ENGINE HAD OCCURRED.  THE PARTS WERE SHIPPED TO AWI AND RECEIVED FEB. 17, 2006, THERE ARE SOME SCREENS THAT HAVE BEEN PERFORATED.  BUT, THE INLET SCREENS DO NOT APPEAR TO HAVE BEEN IN SERVICE.  THE RUBBER AROUND THE INLET SCREENS IS NOT BURNED FROM ENGINE HEAT AND THE SCREENS ARE NOT BLACKENED.  AEROSPACE WELDING TAKES THIS MATTER VERY SERIOUSLY AND A MATERIAL REVIEW BOARD MEETING HAS BEEN CALLED FOR MONDAY AFTERNOON FEB 20,2006 TO REVIEW AND RESOLVE THIS MATTER AS SOON AS POSSIBLE.                                                                     
20060613000052006061300005GL  2006       6          13         CA060220004      120060208G2730C2TP199         HINGE PIN                               DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE                              STABILIZER      WRONG PART      W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       19966                                                          DURING A ROUTINE 100 HOUR INSPECTION, ALL FOUR ELEVATOR HINGE PINS WERE FOUND TO BE HOMEMADE.  AIRCRAFT WAS RECENTLY IMPORTED FROM VENEZULA.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H71 3R3  RRCA806    5E1                  
20060619001912006061900191WP  2006       6          19         CA060220005      120060215G6220369H120351G     LINK                        369D21200503HUGHES369   369D        4470706WP                                                               M/R HUB         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2156       022222520                                           (CAN) DURING A 100 HOUR INSPECTION THE ENGINEER NOTICED A CRACK ON ONE OF THE EARS OF THE LEAD LAG LINK OF THE MAIN ROTOR HUB ASSEMBLY.  CRACK PROPAGATED FROM THE BUSHING OUTWARD. (TC NR 20060220005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1G71 3U      H3WE                         
20060613000062006061300006GL  2006       6          13         CA060221001      120060208G5711C2W927A         SPAR            DHAV        DHC2L20     DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE                              LT WING         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       21602      579                                                 DURING MAINTENANCE (WING REMOVAL) FRONT SPAR WEB FOUND CRACKED AT ROOT FITTING.  ONCE DOUBLER WAS REMOVED, THE CRACK WAS FOUND TO HAVE BEEN STOP DRILLED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3R3  RRCA806    5E1                  
20060613000082006061300008GL  2006       6          13         CA060221002      120060208G5720C2FS537A        CHANNEL                                 DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE                                              WRONG PART      W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA       19966                                                          FOUND CHANNEL ASSEMBLY WAS MADE FROM APPROXIMATELY .125 STEEL.  CHECKED WITH VIKING AND WAS INFORMED THAT CHANNEL IS .080 ALUMINUM.  AIRCRAFT WAS RECENTLY IMPORTED FROM VENEZULA.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3R3  RRCA806    5E1                  
20060613000102006061300010NE  2006       6          13         CA060221003      220060220G73208061532         HMU                                     AIRBUSA321  A321211     3930370EU  GE    CFM56 CFM56*      13802NE                              NR 2 ENGINE     MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 F  FLT CONT AFFECTED                                                             CLCLIMB          1                      CA                                                                      AFTER T/O YOW EN ROUTE YVR ENG 2 COMPRESSOR VANE MSG SEVERAL TIMES DURING FLIGHT.  CREW ELECTED TO DIVERT TO YUL.  ACFT ROUTED TO BASE FOR INVEST.  HMU REPLACED AS PER T/S.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F4  FRTA28NM   E2GL                 
20060613000112006061300011GL  2006       6          13         CA060221004      120060208G2730C2CF619A        ROD                                     DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE                              ELEVATOR        CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       19966                                                          FOUND ELEVATOR ROD ASSEMBLY RUSTY AD HOLES RUSTED THROUGH TUBE AND WHEN ROD END WAS REMOVED SEVERAL TEASPOONS OF RUSTED METAL FLAKES CAME OUT OF THE TUBE, FOUND DURING AN EXTENSIVE 100 HOUR INSPECTION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3R3  RRCA806    5E1                  
20060613000122006061300012SW  2006       6          13         CA060221006      120060211G54102762019111      PANEL                                   SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP                              RT NACELLE      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       24794                                                          WHILE UN-COWLING, RT ENGINE MAINTEANCE FOUND A PIECE OF STAINLESS STEEL IN THE LOWER SECTION OF COWL.  INVESTIGATION REVEALED A HOLE IN THE LT SIDE OF ASPIRATOR ASSEMBLY ABOVE THE OIL COOLER.  THE ASPIRATOR WAS REPLACED AND AIRCRAFT SINCE RETURNED TO SERVICE.  THE MOST PROBABLE CAUSE WOULD BE FATIGUE CRACKING LEADING TO THE PIECE FALLING INTO THE LOWER COWLING.                                                                                                                                                                                                                                                                                                                                                                     2L72 4T4  TRTA8SW    E4WE                 
20060619002072006061900207EU  2006       6          19         CA060221007      120060204G6730SC5083          SERVO                                   SNIAS 350   AS350BA     8680817EU  TMECA ARRIELARRIEL1B    6OO30NE                              FLT CONTROLS    FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       5759 1753                                                      (CAN) ON GROUND RUN: WHEN HYDRAULIC TEST PUSH BUTTON DEPRESSED AND ACCUMULATORS EMPTY, THE CYCLIC WOULD MOVE HARD TO THE LEFT.  SWITCHED LT SERVO AND RT SERVO.  THIS PROBLEM MOVED WITH SERVO TO THE RT SIDE.  INSTALLED A NEW OVERHAUL SERVO ON THE RT SIDE WHICH CLEARED UP OUR PROBLEM.  AC HYDRAULIC SYSTEM NOW OPERATES IAW TYPE.  (TC NR 20060221007)                                                                                                                                                                                                                                                                                                                                                                                    1G71 3U3  UNCH9EU    E19EU                
20060613000402006061300040    2006       6          13         CA060221008      320060209G6111W69EK763        BLADE                                   DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO                              PROPELLER       CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA       1851       AE7827                                              DURING PRE-FLIGHT INSPECTION, THE PILOT INSTRUCTOR DISCOVERED A POSSIBLE CRACK ON THE PROPELLER.  CLOSER INSPECTION REVEALED AN APPROXIMATELY 4" CRACK ON NR 2 BLADE OF PROPELLER.  THE CRACK IS DEVELOPED LONGITUDINAL ON BLADE FROM TIP TO HUB.  NO IMPACT MARK OR OTHER DAMAGE TO PROPELLER OBSERVED.  PROPELLER REMOVED FROM SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                       1L71 3O3  ONTTA4CH   E7SO                 
20060613001622006061300162SW  2006       6          13         CA060221009      120060213G7603C8102419        CONTROL CABLE                           SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP  HARTZLHCB3T HCB3TN5     GL  POWER LEVER     FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      CREW ATTEMPTED TO START THE ENGINE ON 4TH LEG OF THE DAY.  ENGINE ACCELERATED TO 30 PERCENT AND TEMPERATURE INCREASED.  ENGINE WAS SHUT DOWN.  MAINTENANCE DISCOVERED THE POWER LEVER CABLE HAD SEVERED IN THE PEDASTAL AND THE ENGINE WAS STUCK IN FULL REVERSE.  (REVERSE IS SELECTED ON SHUTDOWN TO PUT THE PROPS ON THE START LOCKS).  THE CABLE WAS REPLACED WITH A SERVICEABLE PART AND THE ENGINE PERFORMED NORMALLY.                                                                                                                                                                                                                                                                                                                    2L72 4T4  TRTA8SW    E4WE    6  CP15EA    
20060613001642006061300164GL  2006       6          13         CA060221010      120060216G24102224121400      BRACKET                                 DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO                              ALTERNATOR      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       550                                806495                      DURING ROUTINE INSPECTION, A SMALL CRACK WAS DISCOVERED ON THE ALTERNATOR BRACKET.  FURTHER INSPECTION REVEALED THAT THE TOP NUT TCM P/N 2443 WHICH IS USED TO MOUNT THE BRACKET TO THE ENGINE WAS STRIPPED.  THE NUT ATTACHES TO ONE OF THE ENGINE THRU STUDS AT THE FORWARD MAIN BEARING.  LUCKILY THE STUD WAS NOT DAMAGED AND A NEW BRACKET AND NUT WERE INSTALLED AND TQ`D.  IT WAS ALSO NOTED THAT ALT BRACKET MOUNTING HOLES ARE LARGER THAN THE STUDS AND BOLT USED TO SECURE THE BRACKET TO ENG.  THESE WERE TAUGHT AT FIRST TO BE ELONGATED BUT THE NEW BRACKET SUPPLIED BY THE MANUFACTURE REVEALED THEY WERE MANUFACTURED THIS WAY.  A REQUEST WAS SENT TO THE MANUFACTURE FOR EXPLANATION.                                         1L71 3O3  ONTTA4CH   E7SO                 
20060613001662006061300166NM  2006       6          13         CA060221011      120060220G271085711570102     BRACKET                                 DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF15      NE  AILERON         CRACKED         W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             CRCRUISE         1                      CA       3531435314                                                     DURING CRUISE FLIGHT, CREW REPORTED AILERON CONTROL SEEMED STIFF.  AFTER NORMAL LANDING MAINTENANCE INSPECTION FOUND RT AILERON SUPPORT BRACKET FOR AILERON INPUT QUADRANT CRACKED.  CAUSING OUTBOARD AILERON QUADRANT TO RUB ON BRACKET.  THIS AIRCRAFT IS PRE MOD 8/2160.  DEHAVILLAND SB 8-57-27 REFERS TO THIS BRACKET CRACKING.                                                                                                                                                                                                                                                                                                                                                                                                            2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060613001672006061300167EA  2006       6          13         CA060221012      220060220G852018810           CAMSHAFT                                PIPER PA28  PA28140     7102802SO  LYC   O320  O320E3D     41508EA  SNSNCH74D   74DM        EA  ENGINE          SPALLED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            2396                                                      SPALLING ON CAM AND LIFTERS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L71 3O3  O  2A13    E274    5  NP88614   
20060613001682006061300168SW  2006       6          13         CA060222001      120060217G2820206061677001    LINE                                    BELL  206   206B        1181511SW                                                               FUEL SYSTEM     CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      ON REINSTALLATION OF FUEL LINES IN FUEL VALVE COMPARTMENT TUBE ASSY WAS TORQUED AND FERRULE WAS FOUND TO BE CRACKED.  TUBE ASSY WAS SUSPECTED TO BE CRACKED ON REMOVAL BUT NO LEAKS DETECTED.  LINE REMOVED FROM SERVICE.  RECOMMEND BETTER VISUAL INSPECTION OF ALUMINUM LINES AND PROPER TORQUE PROCEDURES.                                                                                                                                                                                                                                                                                                                                                                                                                                   1G71 3U      H2SW                         
20060614000392006061400039NE  2006       6          14         CA060222002      320060222G611472429           BOLT            HAMSTD                  CNDAIRCL215 CL2151A10   1900320EA  PWA   R2800 CA3         52026NE  HAMSTD43E   43E60       NE  PROP BARREL     SHEARED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            656                                                       ON RE-ASSEMBLY OF A 43E60-583 PROPELLER, THE TORQUE SEQUENCE OF THE BARREL BOLTS WAS BEING ACCOMPLISHED AS PER CANADAIR MAINTENANCE MANUAL SUPPLEMENT 61-10-51. WHEN TORQING ONE OF THE BARREL BOLTS P/N 72429, THE HEAD SHEARED OFF OF THE BOLT SHANK JUST AS MAXIMUM TORQUE WAS BEING REACHED.  IT WAS OBSERVED THAT THE WEIGHT INSERT IN THE MIDDLE OF THE BOLT WAS CORRODED AND COULD BE THE CAUSE OF THE HEAD SHEARING.                                                                                                                                                                                                                                                                                                                    2H72 4R4  RRTA14EA   E231    6  CP871     
20060613001902006061300190CE  2006       6          13         CA060223001      120060223G2510051421518       SEAT BACK                               CESSNA172   172R        2072401CE  LYC   IO360 IO360L2A         EA  MCAULY1C235 1C235LFA    GL  COCKPIT         DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3880                                                           WHILE PERFORMING NORMAL MAINTENANCE IT WAS NOTED THAT THE PILOTS SEAT BACK WAS TILTED MORE ON THE LEFT THAN THE RIGHT.  THE SEAT WAS REMOVED AND THE MATERIAL WAS REMOVED FROM THE SEAT BACK WHICH REVEALED A CRACKED SEAT BACK FRAME AT THE PIONT WERE THE ALUMINUM SEAT MOUNT CASTING ENDS IN THE SQUARE ALUMINUM TUBING WHICH FORMS THE SEAT BACK.                                                                                                                                                                                                                                                                                                                                                                                           1H71 3O3  ONT3A12    1E10    5  NP12EA    
20060613002942006061300294CE  2006       6          13         CA060223002      120060222G3245302039402       TUBE                                    BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA                              TIRE            SPLIT           W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA                                                                      A NORMAL LAND UP UNTIL, SENSED WHAT FELT LIKE DRAGGING BRAKE ON RT M/G.  ONCE SAFELY STOPPED, AND ENG`S SHUT DOWN, CREW EXITED A/C, DISCOVERED RT O/B WHEEL ASSY FLAT TIRE.  RETURNED TO A/C TO FIND TWO OTHER TIRES FLATTENED.  THESE WERE BOTH RT AND LT INBDS TIRES. PLANE RETURNED TO BASE.  ONCE THE WHEEL ASSEMBLIES WERE TAKEN APART FOR TIRE/TUBE REPLACEMENT, DISCOVERED INNER TUBES HAD SPLIT IN A RADIAL DIRECTION ACROSS TUBE.  THE FOLLOWING MORNING, MX FOUND 4TH MAIN WHEEL, THE ONE NOT PREVIOUSLY REPLACED,  ALSO LOST IT'S AIR OVERNIGHT.  A SIMILAR SPLIT WAS FOUND IN INNER TUBE.  ALL 4 WHEELS WERE NEW JUDGING FROM CONDITION.  A/C FLEW DURATION OF FLT IN EXTREME COLD CONDITIONS (-40'C) AT FL 230.                    1L72 4T4  T  A24CE   E4EA                 
20060613002952006061300295CE  2006       6          13         CA060223003      120060220G273126612159        ACTUATOR                                CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE  HARTZLHCB3T HCB3TN3     GL  ELEVATOR TRIM   FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      ELEVATOR TRIM SCREW JACK FAILED ON INSTALLATION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1H71 3T3  T  A37CE   E4EA    6  CP15EA    
20060614000022006061400002CE  2006       6          14         CA060223004      120060220G273026612159        JACKSCREW                               CESSNA208   208B        2073701CE  PWA   PT6   PT6A114     52043NE  HARTZLHCB3T HCB3TN3     GL  ELEVATOR TRIM   FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      ELEVATOR TRIM SCREW JACK (RT) FAILED ON INSTALLATION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1H71 3T3  T  A37CE   E4EA    6  CP15EA    
20060614000042006061400004CE  2006       6          14         CA060223005      120060223G523026012031        SPRING                                  CESSNA208   208B        2073701CE                                                               DOOR LATCH      WEAK            W      A   UNSCHED LANDING                                                                                 E  VIBRATION/BUFFET                                                              CLCLIMB          1                      CA       5337                                                           AIRCRAFT DEPARTED AND AFTER TAKEOFF, ATC INFORMED THE PILOT THAT THE AFT POD CARGO DOOR WAS OPEN.  THE AIRCRAFT RETURNED AND THE PILOT IN COMMAND INSPECTED THE DOOR, HINGES AND AND THE POD AND FOUND NO DAMAGE.  THE AIRCRAFT DEPARTED AND MAINTENANCE INSPECTED THE DOOR AND FOUND THE DOOR SERVICEABLE.  FOUND THE AFT LATCH SPRING WEAK AND REPLACED SPRING AS A PRECAUTION.                                                                                                                                                                                                                                                                                                                                                               1H71 3T      A37CE                        
20060614000062006061400006NM  2006       6          14         CA060224001      120060216G573085720062010     SKIN                                    DHAV  DHC8  DHC8*              NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  RT WING LE      DEPARTED        W      A   UNSCHED LANDING                                                                                 D  INFLIGHT SEPARATION                                                           CLCLIMB          1                      CA       28716                                                          DURING TAKEOFF THE AIRCRAFT LOST THE RT INBOARD LEADING ASSY 611AR UPON ROTATION.  THE LEADING EDGE SECTION REPORTEDLY BLEW OFF, AND OVER THE TOP OF THE WING AND CAME DOWN WITHIN THE AIRPORT BOUNDARY AREA TOWARDS THE END OF THE RUNWAY.  THE AIRCRAFT WAS ABLE TO PERFORM A CIRCUIT AND LANDED SAFELY.  ENGINEERING INSPECTED THE AIRCRAFT AND REPORTED THAT THE UPPER LEADING EDGE ATTACHMENT SCREWS WERE STILL IN PLACE AFTER LANDING, BUT ONLY TWO OF THE 26 LOWER ATTACHMENT SCREWS WERE IN PLACE.  ONE SCREW WAS LOCATED TOWARDS THE INBOARD SIDE AND ONE AT THE OUTBOARD SIDE.  THE OTHER 24 ATTACHMENT SCREWS WERE MISSING.                                                                                                         2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060614000102006061400010SW  2006       6          14         CA060224002      120060217G6700                CYCLIC CONTROL                          BELL  427   427         1182207SW                                                               COCKPIT         OBSTRUCTED      W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             LDLANDING        1                      CA                                                                      CYCLIC STICK FWD MOVEMENT RESTRICTED BY T/R PEDAL STOP MECHANISM CABLE.  T/R PEDAL STOP MECHANISM CABLE BRACKET 427-001-296-103 FOUND MISLOCATED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1G71 3U      R00001RC                     
20060614000122006061400012GL  2006       6          14         CA060224003      220060222G732184250077        FUEL CONTROL                            BELL  206   206L1       1182107SW  ALLSN 250C  250C30      03013GL                              ENGINE          FAILED          W      E   ENGINE SHUTDOWN                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  LDLANDING        1                      CA            597                           CAE895012                   ON A TWO MINUTE COOL DOWN AFTER ONE HOUR FLIGHT, THE ENGINE STARTED TO SURGE, THE PILOT SHUTDOWN THE ENGINE AND AFTER A MOMENT TRIED A RESTART BUT IT WOULD NOT LIGHT-OFF.  THE ENGINEER FOUND NO FUEL WOULD COME OUT OF FCU.  FCU WAS REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1G71 3U3  U  H2SW    E1GL                 
20060614000142006061400014CE  2006       6          14         CA060224004      120060222G561010138402522     WINDSHIELD                              BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA                              COCKPIT         FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA                                                                      WHILE IN CRUISE FLT AT FL 270, APPROXIMATELY 250 MILES INTO THE MIDDAY FLT, FLIGHT CREW REPORTED HEARING A MILDLY LOUD BANG WITHIN THE CABIN.  THEY THEN NOTICE SMALL SHARDS OF GLASS FALLING ONTO THE LAP OF THE FIRST OFFICER.  THE INNER PANE OF THE RIGHT WINDSHIELD HAD SHATTERED.  THE CREW INITIATED THE STANDARD PROCEDURE FOR A CRACKED WINDSHIELD IAW THE POH BY REDUCING THEIR CRUISE SPEED, DESCENDED TO 14000 FEET AND REDUCE CABIN DIFFERENTIAL TO 4.0 PSI.  THE FIRST OFFICER DONED HIS GOGGLES AND THEY RETURNED  SAFELY.  THE WINDSHIELD WAS REPLACED AND THE AIRCRAFT WILL BE RETURNED TO SERVICE UPON COMPLETING THE CURE TIME FOR THE SEALANT.  NOTE THAT THE OAT AT THE TIME OF THE FLIGHT AT 270 WAS -47'C.               1L72 4T4  T  A24CE   E4EA                 
20060619002322006061900232NE  2006       6          19         CA060224005      220060207G7200                ENGINE                                  SNIAS 350   AS350BA     8680817EU  TMECA ARRIELARRIEL1B    6OO30NE                                              FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                          4272                        IN(CAN) AIR OPERATOR:   MODULE 3: CENTRIFUGAL COMP. INDUCER PN 0292251370 S/N 1260FT LIFE LIMIT 14000CYC ACTUAL 14711CYC. CENTRIFUGAL COMP. IMPELLER PN 2292252980 S/N 1019FB LIFE LIMIT 14000CYC ACTUAL 14711CYC. REF: MM NR 29201931, CHAP 05-10-03 PAGE 9 (OCT 2003).  MODULE 4: FREE TURBINE DISK PN 2292802500 S/N ADB4234YC LIFE LIMIT 10000CYC ACTUAL 10727CYC. REF: MM NR 29201931, CHAP 05-10-03 PAGE 10 (DEC 1996).  (TC NR 20060224005).                                                                                                                                                                                                                                                                                             1G71 3U3  UNCH9EU    E19EU                
20060614000192006061400019EA  2006       6          14         CA060224006      220060215G7414LW15416         ADAPTER                                 HUGHES269   269C1       8059504SW  LYC   O360  HO360C1A    41514EA                              RT MAGNETO      BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      DURING 25 HOUR INSPECTION, OIL WAS DRAINED FROM ENGINE AND FOUND BEARING CAGE BALL RETAINER MADE OF PLASTIC (KIND OF) ON ENGINE OIL SCREEN.  REMOVED BOTH MAGNETO DRIVE ADAPTER ASSEMBLY AND FOUND THE PROBLEM ON THE RT ADAPTER (BALL RETAINERS MISSING).  REPLACED THE PART P/N LW15416.                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3O3  OO 4H12    E286                 
20060614000732006061400073    2006       6          14         CA060224007      420060216G2562                SWITCH          POINTER                 ROBSINR22   R22BETA     7640110NM  LYC   O320  O320B2C     41508EA                              ELT             FAILED          W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA                  408804                                              WHEN THE PILOT ACTIVATE THE ELT REMOTE SWITCH IN THE CABIN, THE ELT FAIL TO ACTIVATE.  REPLACED ELT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1G71 3O3  O  H10WE   E274                 
20060614000752006061400075CE  2006       6          14         CA060224008      120060224G2710MS21251B5S      TURNBUCKLE      CESSNA                  CESSNA650   650         2076802CE  GARRTTTPE731TFE7313C         WP                              CONTROL CABLES  CHAFED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       5899                                                           DURING A SCHEDULED PHASE 5 INSPECTION ON CESSNA 650 C-FIMO, THE TECHNICIAN DISCOVERED THAT THE LT AND RT AILERON OUTBOARD AFT CABLE CHAFED THROUGH THE LOKCLAD AND THE TURNBUCKLE WAS DAMAGED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F4  F  A9NM    E6WE                 
20060614000762006061400076CE  2006       6          14         CA060224009      120060224G2510051402133       SEAT                                    CESSNA172   172N        2072434CE  LYC   O320  O320D2J     41508EA  MCAULY1C160 1C160DTM    GL  COCKPIT         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       11104                                                          WHILE DOING 100HR INSPECTION ON AIRCRAFT AME WAS DOING THE SEAT RAIL INSPECTION NOTICED PILOTS SEAT WAS LOOSE WHEN HE MOVED IT BACK. ON FURTHER INSPECTION OF THE SEAT IT WAS DISCOVERED THAT ONE OF THE ATTACHMENT LEGS USED TO ATTACH THE SEAT TO THE PEDESTAL WAS CRACKED AND ONE OF THE LEGS WAS BROKEN.  SEAT WAS REMOVED AND NEW PARTS ORDERED.                                                                                                                                                                                                                                                                                                                                                                                           1H71 3O3  ONT3A12    E274    5  NP910     
20060614000772006061400077CE  2006       6          14         CA060224010      120060222G754042302200        SWIVEL          LEAR                    LEAR  45    45LEAR      5170805CE  GARRTTTFE731TFE7312     01518WP                              PYLON DUCT      LEAKING         W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA       1467                                                           ENGINE PYLON DUCT OVERHEAT CAS MESSAGE LIGHT ILLUMINATED 25 MINUTES INTO FLIGHT.  AIRCRAFT RETURNED TO BASE.  ENGINE GROUND RAN AND FOUND THAT LIGHT EXTINGUISHES WITH POWER BELOW 50%.  PYLON DUCT REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  FRTT00008WIE6WE                 
20060614000792006061400079CE  2006       6          14         CA060224011      120060223G335065181097        BATTERY PACK                            CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              EMERGENCY LIGHT CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      DURING A PHASE INSPECTION, EMERGENCY LIGHT OPERATIONAL CHECK, THE LIGHTS FAILED TO TURN ON.  FURTHER INVESTIGATION REVEALED THAT THE EMERGENCY LIGHT POWER SUPPLY WAS DAMAGED.  ALL BATTERIES CELLS WERE CORRODED AND THE BATTERY BOX MELTED.  THE BATTERY PACK 2 AMP FUSE CHECKED SERVICEABLE.  BATTERY PACK WAS REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                     1L72 4F4  F  A22CE   E1NE                 
20060614000942006061400094NM  2006       6          14         CA060227001      120060226G324021599           BRAKE ASSY                              DHAV  DHC8  DHC8*              NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF23      NE  RT MLG          LEAKING         W      O   OTHER                                                                                           KA FLUID LOSS                FLAME/FIRE                                          LDLANDING        1                      CA                                                                      BRAKES ON RT MLG CAUGHT FIRE DURING LANDING AND CAUSED A 'FLASH FIRE'.  FIRE WAS CAUSED BY FLUID LEAKING FROM BRAKE UNIT AND COMING INTO CONTACT WITH HOT BRAKING SURFACE.  AN OFF-DUTY PILOT WITNESSED INCIDENT FROM PAX CABIN AND REPORTED FIRE WAS A 'FLASH BALL' THAT EXTINGUISHED ALMOST IMMEDIATELY.  A/CS FWD MOTION AND PROP WASH BLEW SMOKE AND FLAMES AFT. BOTH TIRES BLEW, FIRE DEPART WERE ON SCENE APPROX 3 MINS AFTER INCIDENT AND COOLED GEAR DOWN, INITIALLY WITH A MIST AND THEN WITH A SPRAY AND THEN A FAN WAS USED TO FURTHER REDUCE TEMP. TEMP READING TAKEN APPROX 23 MINS AFTER INCIDENT SHOWED 350 DEGREES F.  A TEMP READING TAKEN A FURTHER 10 MINS LATER SHOWED 240 DEGREES F.  A VISUAL INSPECTION OF LWR END OF DR2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060614000952006061400095SW  2006       6          14         CA060227002      120060223G5320206032319023    STIFFENER                               BELL  206   206L        1181522SW  ALLSN 25OC  250C20R          GL                              FUSELAGE        CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      AFTER REMOVAL OF AFT FUSELAGE FAIRING FOR REPAIR.  VISUAL INSPECTION AND CLEANING OF AFT FUSELAGE A STIFFENER FOUND CRACKED.  STIFFENER REPLACED NEW.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1G71 3U3  U  H2SW    E4CE                 
20060614000962006061400096NE  2006       6          14         CA060227003      220060221G7200PW121           ENGINE                                  DHAV  DHC8  DHC8*              NM  PWA   PW121 PW121       52124NE  HAMSTD14SF  14SF7       NE  NR 1            FAILED          W      O   OTHER                                                                                           XJ ENGINE FLAMEOUT           WARNING INDICATION                                  DEDESCENT        1                      CA                                          PCE121280                   DURING DESCENT AN OPERATOR EXPERIENCED AN INCIDENT IN SEVERE TURBULENCE WHERE BOTH PROPELLERS/ENGINES WERE OVERSPEED.  THE NR 1 ENGINE HAD THE TORQUE SHAFT BREAK AND THE POWER TURBINE BLADES SEPARATE.  BOTH PROPELLERS/ENGINES TO BE REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060614000972006061400097NE  2006       6          14         CA060227004      220060122G7200                TURBINE BLADES                          CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE  HARTZLHCB3T HCB3TN3     GL  ENGINE          DAMAGED         W      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  NRNOT REPORTED   1                      CA                                          19352                       THE PILOT REPORTED A LOSS OF ENGINE POWER AND ATTEMPTED A FORCED LANDING.  THE AIRCRAFT CRASHED DURING THE ATTEMPT.  PRELIMINARY INVESTIGATION HAS REVEALED TURBINE BLADE DISTRESS.  P&WC WILL INVESTIGATE THE INCIDENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1H71 3T3  T  A37CE   E4EA    6  CP15EA    
20060614000982006061400098    2006       6          14         CA060227005      120060224G71206898806         SUPPORT                                                                    ALLSN 250C  250C28B     03013GL                              ENGINE          CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       8132 1314                                                      ON REMOVAL OF TURBINE SECTION FROM ENGINE ASSY ONE OF THE FWD SUPPORT STUTS WAS FOUND TO BE CRACKED.  TURBINE ASSY SENT FOR REPAIR.  RECOMMEND BETTER VISUAL INSPECTIONS ON SCHEDUELED INSPECTIONS AND POSSIBLY VIBRATION CHECKS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      3  U          E1GL                 
20060614001732006061400173NE  2006       6          14         CA060227006      220060130G732141380102        FUEL CONTROL                            PIPER PA46  PA46500TP   7104622SO  PWA   PT6   PT6A42      52043NE                              ENGINE          MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 R  PARTIAL RPM/PWR LOSS                                                          CRCRUISE         1                      CA                                                                      THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION IN CRUISE AND WOULD NOT RESPOND TO THROTTLE LEVER INPUT.  THE PILOT ACTIVATED THE FUEL CONTROL MANUAL OVER-RIDE AND ACCOMPLISHED AN UNSCHEDULED LANDING.  GROUND INSPECTION COULD NOT DUPLICATE THE INCIDENT.  THE FUEL CONTROL UNIT WAS SUBSEQUENTLY REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                           1L71 3O4  TRTA25SO   E4EA                 
20060614002072006061400207NE  2006       6          14         CA060227007      220060111G7321                FUEL CONTROL                            PILATSPC12  PC12        7090550EU  PWA   PT6   PT6A67B     52043NE                              ENGINE          FAILED          W      O   OTHER                                                                                           RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  NRNOT REPORTED   1                      CA                                          PR0565                      DURING AIRCRAFT FLIGHT TESTING, THE ENGINE DID NOT RE-LIGHT FOLLOWING A COMMANDED INFLIGHT SHUT DOWN FOR RE-LIGHT TEST PURPOSES.  A DEAD STICK LANDING WAS ACCOMPLISHED.  THE FUEL CONTROL UNIT AND FLOW DIVIDER VALVE WERE SUBSEQUENTLY REPLACED.  P&WC WILL MONITOR INVESTIGATION OF THE INCIDENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                             1L71 3T4  TRTA78EU   E26NE                
20060614002092006061400209NE  2006       6          14         CA060227008      220060129G7200                ENGINE                                  AEROSPATR72 ATR72              EU  PWA   PW120 PW127            NE                                              MALFUNCTIONED   W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA                                          EB0011                      IN CRUISE, THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION ACCOMPANIED BY AN UNCOMMANDED INCREASE IN PROP SPEED.  THE ENGINE WAS SHUT DOWN IN FLIGHT.  GROUND INSPECTION WAS UNABLE TO DUPLICATE THE PROBLEM.  THE ENGINE FUEL CONTROL UNIT, FUEL PUMP, FADEC, ELECTRICAL HARNESS AND TORQUE SENSOR WERE SUBSEQUENTLY REPLACED.  P&WC WILL MONITOR INVESTIGATION OF THE INCIDENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                          2H72 4T4  TRT        E20NE                
20060614002112006061400211EU  2006       6          14         CA060227009      120060203G7930                WARNING LIGHT                           AEROSPATR72 ATR72              EU  PWA   PW120 PW127            NE                              ENGINE OIL SYS  ILLUMINATED     W      E   ENGINE SHUTDOWN                                                                                 N  FALSE WARNING                                                                 CRCRUISE         1                      CA                                          EB0078                      DURING CRUISE, THE ENGINE LOW OIL PRESSURE WARNING ANNUNCIATED.  THE ENGINE WAS SHUT DOWN IN FLIGHT.  SUBSEQUENT GROUND TESTING WAS UNABLE TO DUPLICATE THE EVENT.  THE OIL PRESSURE TRANSMITTER AND LOW OIL PRESSURE SWITCH WERE REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                2H72 4T4  TRT        E20NE                
20060614002122006061400212NE  2006       6          14         CA060227010      220060204G7230                COMPRESSOR                              CESSNA208   208         2073702CE  PWA   PT6   PT6A114     52043NE                              ENGINE          SEIZED          W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                          PR0508                      THE ENGINE ACCESSORY GEARBOX CHIP DETECTOR WARNING ANNUNCIATED IN FLIGHT AND AN UNSCHEDULED LANDING WAS CARRIED OUT.  SUBSEQUENT INSPECTION REVEALED SEIZURE OF THE COMPRESSOR SECTION.  P&WC WILL INVESTIGATE THE INCIDENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1H71 3T3  TNTA37CE   E4EA                 
20060614002142006061400214EU  2006       6          14         CA060227011      120060225G323019071100403     RELEASE ACTUATOR                        EMB   ERJ170ERJ170100LR        EU  GE    CF34  CF348E5A1   30015NE                              MLG DOWNLOCK    MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      LEFT MAIN GEAR DID NOT RETRACT AFTER TAKEOFF.  NO GEAR PIN ON MAIN WERE FOUND ON ARRIVAL, PARK BRAKE REMAINED ON AFTER BRAKE HANDLE RELEASED.  LT MLG DOWNLOCK RELEASE ACTUATOR REPLACED IAW AMM 32-31-05-000-801-A AND 32-31-05-400-801-A.  GEAR SWING CARRIED OUT AS PER AMM 32-33-00-710-801-A.  ALL FUNCTIONS NORMAL.                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F4  FRTA56NM   E00063EN             
20060614002152006061400215NE  2006       6          14         CA060227012      220060201G7210                PACKING                                 AEROSPATR42 ATR42320    8680930EU  PWA   PW121 PW121       52124NE                              RGB OIL SYS     CUT             W      E   ENGINE SHUTDOWN                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  NRNOT REPORTED   1                      CA                                                                      THE ENGINE LOW OIL PRESSURE WARNING ANNUNCIATED AND THE ENGINE WAS SHUT DOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED A CUT O-RING PACKING AT THE PROPELLER CONTROL UNIT ADAPTER INTERFACE TRANSFER TUBE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2H72 4T4  TRTA53EU   E20NE                
20060614002172006061400217EU  2006       6          14         CA060227013      120060210G7810                EXHAUST DUCT                            UROCOPEC135 EC135P1     8680990EU  PWA   PW206 PW206B      0    NE                              ENGINE          FRACTURED       W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      DURING FLIGHT, A LOUD WHISTLING NOISE WAS REPORTED BY THE CREW.  SUBSEQUENT INSPECTION REVEALED THE ENGINE-MOUNTED AIRFRAME EXHAUST DUCT HAD FRACTURED AND LIBERATED WITH RESULTANT DAMAGE TO THE MAIN ROTOR AND VERTICAL FIN.  P&WC WILL MONITOR THE INVESTIGATION OF THE INCIDENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED.                                                                                                                                                                                                                                                                                                                                                                                                              1G72 3U3  UO H88EU   E42NE                
20060614002182006061400218NE  2006       6          14         CA060227014      220060210G7200                ENGINE                                  CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                                              FLAMED OUT      W      O   OTHER                                                                                           XJ ENGINE FLAMEOUT           WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA                                          71397                       THE ENGINE FLAMED OUT DURING TAXI.  SUBSEQUENT INVESTIGATION COULD NOT DUPLICATE THE PROBLEM.  THE ENGINE FUEL FILTER WAS REPLACED, THE AIRFRAME RIGGING CHECKED AND THE AIRCRAFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L72 4F4  F  A22CE   E1NE                 
20060614002202006061400220SO  2006       6          14         CA060227015      120060223G5740                MOUNT                                   PIPER PA12  PA12        7101202SO  LYC   O320  O320A2B     41508EA  MCAULY1A175 1A175GM     GL  AFT FLAP PULLEY FAILED          W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             CLCLIMB          1                      CA                                                                      FLAP PULLEY MOUNT INSTALLED IN AFT FUSELAGE CABIN AS PER STC SA578AL AT UNKNOWN TIME, FAILED IN FLIGHT.  MOUNT WAS WELDED TO FUSELAGE BRACE TUBE 5/8".035 WALL.  TUBING FATIGUED AROUND WELD AND PULLEY MOUNT SHIFTED CAUSING MISALIGNMENT OF PULLEY TO CABLE.  THIS CAUSED THE PULLEY TO SUBSEQUENTLY FAIL ON CLIMB AND A LOSS OF "DOWN" FLAP CONTROL.  THE TUBING AROUND THE WELD APPEARED WORKED DOWN TO .025" BY UNKNOWN PERSON WHO INSTALLED IT.  AIRCRAFT LANDED WITHOUT INCIDENT.                                                                                                                                                                                                                                                        1H71 3O3  O  A780    E274    5  NP857     
20060614002212006061400221EA  2006       6          14         CA060227016      220060206G7200                ENGINE                                  DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A27      52043EA                                              POWER LOSS      W      O   OTHER                                                                                           RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  DEDESCENT        1                      CA                                          50413                       DURING DESCENT, THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY A LOSS IN POWER.  A SINGLE-ENGINE LANDING WAS ACCOMPLISHED.  PWC WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H72 3T4  TRTA9EA    E4EA                 
20060614002222006061400222NE  2006       6          14         CA060227017      220060215G732181850011        FUEL CONTROL                            CESSNA500   550         2076604CE  PWA   530   PW530A           NE                              ENGINE          MALFUNCTIONED   W      E   ENGINE SHUTDOWN                                                                                 F  FLT CONT AFFECTED                                                             DEDESCENT        1                      CA                                                                      DURING DESCENT, THE ENGINE WAS FOUND TO NOT RESPOND TO THROTTLE LEVER INPUT AND WAS SHUT DOWN IN FLIGHT.  THE ENGINE FUEL CONTROL UNIT AND FLOW DIVIDER VALVE WERE SUBSEQUENTLY REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 4F4  F  A22CE   E00053EN             
20060614002242006061400224EA  2006       6          14         CA060227018      220060213G7261                ENGINE                                  EMB   110   EMB110*            SO  PWA   PT6   PT6A28           EA                              OIL SYS         LEAKING         W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         KJ FLUID LOSS                WARNING INDICATION                                  CLCLIMB          1                      CA                                          50036                       DURING CLIMB, THE ENGINE EMITTED A NOISE ACCOMPANIED BY AN UNCOMMANDED REDUCTION IN POWER AND INCREASE IN TURBINE TEMPERATURE.  THE ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  GROUND INSPECTION REVEALED AN ENGINE OIL LEAK.  THE ENGINE HAD BEEN OVERHAULED 100 HOURS PRIOR TO THE EVENT, WHERE IT WAS CONVERTED UNDER STC TO A PT6A-34 CONFIGURATION.  PWC WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                     1L72 4T4  TRTA21SO   E4EA                 
20060614002252006061400225NE  2006       6          14         CA060227019      220060219G7200                ENGINE                                  PILATSPC12  PC12        7090550EU  PWA   PT6   PT6A67B     52043NE                                              MALFUNCTIONED   W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA                                          PR0117                      ON APPROACH, THE ENGINE WAS FOUND NOT TO RESPOND THE THROTTLE LEVER INPUT.  THE PILOT ENGAGED THE FUEL CONTROL MANUAL OVER-RIDE AND REGAINED AUTHORITY OVER THE ENGINE.  P&WC WILL MONITOR THE INVESTIGATION OF THE INCIDENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L71 3T4  TRTA78EU   E26NE                
20060615000032006061500003NE  2006       6          15         CA060227020      220060213G7200                ENGINE                                  CESSNA500   550         2076604CE  PWA   JT15  JT15*       52060NE                                              POWER LOSS      W      E   ENGINE SHUTDOWN                                                                                 ERJVIBRATION/BUFFET          PARTIAL RPM/PWR LOSS      WARNING INDICATION        DEDESCENT        1                      CA                                                                      ON DESCENT, THE ENGINE WAS REPORTED TO EMIT A GRINDING NOISE ACCOMPANIED BY AN UNCOMMANDED POWER LOSS.  THE ENGINE WAS SHUT DOWN IN FLIGHT AND A SINGLE-ENGINE LANDING ACCOMPLISHED AT POINT OF DESTINATION.  GROUND INSPECTION REVEALED INTERNAL ENGINE DAMAGE.  P&WC WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED.                                                                                                                                                                                                                                                                                                                                                                                   1L72 4F4  T  A22CE   E1NE                 
20060615000042006061500004NE  2006       6          15         CA060227021      220060221G7261                LINE                                    CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE                              REDUCTION GBOX  FRACTURED       W      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  NRNOT REPORTED   1                      CA                                                                      DURING FLIGHT, THE ENGINE LOW OIL PRESSURE WARNING ANNUNCIATED FOLLOWED BY AN UNCOMMANDED ROLL BACK IN ENGINE POWER.  THE ENGINE WAS SECURED IN FLIGHT AND A SUCCESSFUL FORCED LANDING ACCOMPLISHED.  SUBSEQUENT INSPECTION REVEALED A FRACTURED PRESSURE OIL TRANSFER TUBE ELBOW.  P&WC WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED.                                                                                                                                                                                                                                                                                                                                                                 1H71 3T3  T  A37CE   E4EA                 
20060615000082006061500008NE  2006       6          15         CA060227022      220060220G7200                ENGINE                                  CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                                              FAILED          W      O   OTHER                                                                                           XJ ENGINE FLAMEOUT           WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      THE ENGINE EXPERIENCED AN UNCOMMANDED IN-FLIGHT SHUT DOWN AFTER TAKEOFF.  SUBSEQUENT INSPECTION REVEALED DEBRIS IN THE ENGINE EXHAUST.  P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L72 4F4  F  A22CE   E1NE                 
20060615000102006061500010CE  2006       6          15         CA060227023      120060224G3230M710501         MOTOR                                   BEECH 90    F90         1152909CE  PWA   PT6   PT6A135     52043NE  HARTZLHCB4T HCB4TN3     GL  NLG             UNSERVICEABLE   W      L   ABORTED APPROACH                                                                                J  WARNING INDICATION                                                            LDLANDING        1                      CA       5160                                                           NOSE GEAR FAILED TO EXTEND CORRECTLY AS INDICATED BY GEAR IN TRANSIT.  GEAR EXTENDED MANUALLY AND LANDED WITHOUT INCIDENT.  CAUSE UNDER INVESTIGATION AT THIS TIME.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L72 4T4  T  A31CE   E4EA    6  CP40EA    
20060615000112006061500011CE  2006       6          15         CA060227024      120060116G7120509800891       MOUNT                                   BEECH 100   A100A              CE  PWA   PT6   PT6A27      52043EA  HARTZLHCB3T HCB3TN3     GL  RT ENGINE       DETACHED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      UPPER INBOARD ENGINE MOUNT FITTING RT NACELLE UNDER SKIN FOUND DETACHED.  SUBSEQUENT INSPECTION OF OTHER FITTINGS ON SAME AIRCRAFT (THERE ARE 4) FOUND ALL WITH ATTACHING FASTENER DEFECTS SUCH AS LOOSE OR SHEARED.  AREA IS ALMOST UN-INSPECTABLE.  SUGGEST BOROSCOPE INSPECTION OR REMOVING A PORTION OF NACELLE SKIN IF ENGINE MOUNT MOVEMENT IS DETECTED IN FITTING AREA.                                                                                                                                                                                                                                                                                                                                                                  1L72 3T4  T  A14CE   E4EA    6  CP15EA    
20060615000122006061500012EA  2006       6          15         CA060228001      120060215G56106003303025      WINDSHIELD                              CNDAIRCL604 CL604       1900301EA  GE    CF34  CF343B1          NE                                              CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA                                                                      WHILE CRUISING THE LT WINDSHIELD OUTER PLY CRACKED.  THE AIRCRAFT CONTINUE INTO WHERE A NEW WINDSHIELD WAS INSTALLED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F4  FRTA21EA   E15NE                
20060615000142006061500014CE  2006       6          15         CA060228002      120060224G30005918411         DIODE                                   LEAR  45    45LEAR      5170805CE  GARRTTTFE731TFE7312     01518WP                              ANTI-ICE SYSTEM FAILED          W      O   OTHER                                                                                           L  NO TEST                                                                       TXTAXI/GRND HDL  1                      CA       2577                                                           DURING PREDEPARTURE CHECK, THE LT ANTI-ICE VALVE FAILED TO OPEN.  DURING TROUBLESHOOTING OF THE SYSTEM FOUND THE DIODE D25 HAD HIGH RESISTANCE PREVENTING THE ANTI-ICE SHUTOFF VALVE TO GET A GROUND WHEN REQUIRED.  NEW DIODE WAS INSTALLED AND SYSTEM FUNCTIONED CHECK NORMAL.                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F4  FRTT00008WIE6WE                 
20060615000162006061500016EU  2006       6          15         CA060228003      120060226G27509028A000201     PICKUP                                  AIRBUS310   A310300     3930305EU  GE    CF6   CF680C2*         GL                              TE FLAPS        CONTAMINATED    W      O   OTHER                                                                                           O  OTHER                                                                         LDLANDING        1                      CA                                                                      AIRCRAFT LANDED WITH FULL SLATS AND NO FLAPS.  UNABLE TO EXTEND FLAPS ON LANDING.  SYSTEM TORQUE LIMITERS AND SCREW JACKS LIMITER INSPECTED AND NO FAULT FOUND.  DURING TROUBLESHOOTING, THE LT AND RT POWER PICK UP UNITS WERE FOUND CONTAMINATED WITH SKYDROL AND READOUTS NOT MEETING THE MM LIMITS.  BOTH UNITS REPLACED AND SYSTEM TESTED SERVICEABLE.                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA35EU   E23EA                
20060615000172006061500017NM  2006       6          15         CA060228004      120060226G3230846802          PSEU                                    BOEING767   767233      1385113NM  PWA   JT9   JT9D7R4D    52054NE                              MLG             MALFUNCTIONED   W      O   OTHER                                                                                           J  WARNING INDICATION                                                            APAPPROACH       1                      CA                                                                      SELECTING LANDING GEAR DOWN, STATUS MSG 'LDG GEAR MONITOR' CAME ON AND REMAINED ON, DURING LANDING, TAXI, AND PARKING.  PSEU CARD FAILED ILLUM.  PSEU REPLACED PER AMM 32-09-04 PB 401.  PSEU BITE TEST OKAY.  MESSAGES CLEARED.  OKAY TO PROCEED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F4  FRTA1NM    E3NE                 
20060615000192006061500019CE  2006       6          15         CA060228005      120060220G273126612159        JACKSCREW                               CESSNA208   208B        2073701CE  PWA   PT6   PT6A114     52043NE  HARTZLHCB3T HCB3TN3     GL  ELEVATOR TRIM   DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      THE LT ELEVATOR TRIM JACK WAS REMOVED AND DISASSEMBLED FOR INSPECTION AFTER THE RT TRIM JACK FAILED ON INSTALLATION.  THE LT TRIM JACK WAS FOUND TO CONTAIN NO GREASE.  THE JACK WAS INSPECTED, LUBRICATED IAW AMM 27-30-02, 9A, REASSEMBLED, TESTED AND RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3T3  T  A37CE   E4EA    6  CP15EA    
20060615001442006061500144    2006       6          15         CA060228006      420060222G34189754421421      VANE            ROSEMOUNT               PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  AOA TRANSMITTER INOPERATIVE     W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            1573  0288                                                DURING A ROUTINE PHASE 5 INSPECTION , THE LT AOA VANE HEATER WAS FOUND TO BE INOPERATIVE.  ASSY REPLACED WITH SERVICEABLE UNIT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20060615001882006061500188EU  2006       6          15         CA060228007      120060119G21609599020135      CONTROL VALVE                           PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  CABIN TEMP      INTERMITTENT    W      D   RETURN TO BLOCK                                                                                 J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      CA            1608  0048                                                TEMPERATURE CONTROL VALVE FOUND TO INTERMITTENTLY STICK AT HOT POSITION CAUSING A DUCT TEMPERATURE WARNING.  VALVE REPLACED WITH SERVICEABLE ASSY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20060615001892006061500189NM  2006       6          15         CA060228008      120060227G291065C265101024    LINE                                    BOEING737   737522      138449FNM  CFMINTCFM56 CFM563C     13802EU                              HYD SYSTEM      CHAFED          W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      FLUID LEAK ON RT GEAR "UP" HYDRAULIC RETURN LINE NOTICED DURING OVERNIGHT CHECK.  LINE WAS CHAFED THROUGH DUE TO RUBBING ON A BRACKET.  LINE REPLACED,GEAR SWING CARRIED OUT AND AIRCRAFT RETURNED TO SERVICE.     TT-37255:17 TC-22887.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F4  FRTA16WE   E21EU                
20060615001912006061500191CE  2006       6          15         CA060228009      120060222G27312661259         JACKSCREW                               CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE                              ELEVATOR TRIM   FAILED          W      K   NONE                                                                                            W OINADEQUATE Q C                                      OTHER                     ININSP/MAINT     1                      CA       8                                                              AS A PRECAUTION FOLLOWING THE FAILURE ON INSTALLATION OF A SIMILAR TRIM JACK ON A DIFFERENT AIRCRAFT, BOTH ELEVATOR TRIM JACKS ON FSKS WERE REMOVED AND DISASSEMBLED TO INSPECT FOR CORRECT LUBRICATION.  THE LT TRIM JACK (S/N CA0009) WAS FOUND TO BE CORRECTLY LUBRICATED.  THE RT TRIM JACK (S/N CA0008) WAS FOUND TO BE DEVOID OF GREASE.  BOTH JACKS WERE CLEANED, INSPECTED, REPACKED WITH GREASE IAW AMM 27-30-02 9A.  REASSEMBLED, FUNCTION TESTED, AND RETURNED TO SERVICE.                                                                                                                                                                                                                                                           1H71 3T3  T  A37CE   E4EA                 
20060615001952006061500195CE  2006       6          15         CA060228013      120060220G3340TTGCTA201TWB    SWITCH                                  CESSNA172   172P        2072436CE  LYC   O320  O320D2J     41508EA  MCAULY1C160 1C160DTM    GL  EXTERIOR LIGHTS SEIZED          W      A   UNSCHED LANDING                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      APAPPROACH       1                      CA                                                                      UPON APPROACH TO LAND, PILOT TURNED ON LANDING LIGHT AND OBSERVED A SMALL AMOUNT OF SMOKE COMING FROM THE SWITCH AND WAS UNABLE TO TURN THE SWITCH OFF DUE TO IT SEIZING IN THE 'ON' POSITION.  TURNED OFF THE AIRCRAFT MASTER SWITCH INSTEAD AND LANDED SAFELY.  THE SWITCH WAS REPLACED.  THE REMOVED SWITCH LOOKED NORMAL ON THE OUTSIDE BUT THE WHITE PORTION WAS SLIGHTLY BLACKENED.                                                                                                                                                                                                                                                                                                                                                       1H71 3O3  ONT3A12    E274    5  NP910     
20060615001972006061500197CE  2006       6          15         CA060228014      120060206G5700                WING                                    CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE  MCAULY3AF34C3GFR34C703  GL  BOTH            MISINSTALLED    W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA                                                                      DURING INSPECTION, FOUND INBD EDGES OF BOTH LT AND RT FLAP ASSEMBLIES WERE TOUCHING FUSELAGE IN FULL UP POSITION.  MX DEPART COMPLETED INSPECTIONS OF FOLLOWING AREAS FLAP ATTACHMENT, FLAP RIGGING, FLAP STRUCTURE FOR BENDING OR WARPING, STRUCTURE OF WINGS FOR BENDING OR WARPING.  NOTHING WAS FOUND.  13 MONTHS PREVIOUS, WINGS WERE REMOVED TO FACILITATE INSPECTIONS FOR CORROSION AND STRUCTURAL DAMAGE.  WHEN WINGS WERE REINSTALLED ATTACHING HARDWARE REPLACED WITH NEW.  REAR ATTACH POINTS OF WINGS ARE ADJUSTABLE TO SET WING AT PROPER ANGLE.  WINGS WERE ADJUSTED OUT AND A TEST FLT WAS COMPLETED.  ALL OTHER CARAVANS IN FLEET WERE INSPECTED, NO FAULTS FOUND.  CESSNA WAS ALSO MADE AWARE OF THE SITUATION.                1H71 3T3  T  A37CE   E4EA    5  CP60GL    
20060615001982006061500198CE  2006       6          15         CA060228015      120060119G71209998000060463   MOUNT                                   BEECH 99    99AFACH            CE  PWA   PT6   PT6A27      52043EA  HARTZLHCB3T HCB3TN3     GL  RT ENGINE       DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       35093                                                          DURING A SCHEDULED DETAILED NR 3 INSPECTION, OBSERVED THE RT ENGINE MOUNT ASSY HAD SEPARATED APPROX 1/4 OF AN INCH FROM RT NACELLE.  LIFTING OF ENG WITH CRANE CONFIRMED MOVEMENT.  VISUAL INSPECTION REVEALED 2 OF THE 4 UPPER INBD BOTTOM ENGINE MOUNT CASTING RIVITS SHEARED. THIS AREA IS DIFFICULT TO INSPECT.  REMOVAL OF THE INBD AND OUTBD NACELLE SKINS IS THE ONLY WAY TO GAIN ACCESS TO THE UPPER CASTINGS FOR INSPECTION WHICH WERE FOUND WITH SIGNS OF RIVET FAILURE.  THE RT ENGINE, PROPELLER, COWLINGS, AND FUSELAGE SUFFERED SUDDEN STOPPAGE DAMAGE BY A DEER STRIKE 125 HOURS PRIOR TO THESE OBSERVATIONS WHICH MAY HAVE ATTRIBUTED IN THIS FAILURE. REPAIRS C/O BY R.D.C.                                                    1L72 3T4  T  A14CE   E4EA    6  CP15EA    
20060615002002006061500200NE  2006       6          15         CA060228016      220060222G7200                ENGINE                                  AEROSPATR72 ATR72              EU  PWA   PW120 PW127            NE                                              FLAMED OUT      W      A   UNSCHED LANDING                                                                                 XJ ENGINE FLAMEOUT           WARNING INDICATION                                  DEDESCENT        1                      CA                                          127025                      ON DESCENT, THE ENGINE FLAMED OUT AND THE PROPELLER FEATHERED.  A RE-LIGHT ATTEMPT WAS UNSUCCESSFUL.  P&WC WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2H72 4T4  TRT        E20NE                
20060615002012006061500201CE  2006       6          15         CA060228017      120060227G7931                OIL SYSTEM                  PW306C      CESSNA680   680CE       2076811CE  PWA   306   PW306B           NE                              ENGINE          LOW             W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                          CG0023                      FOLLOWING TAKEOFF ENGINE OIL PRESSURE DECREASED AND THE ENGINE WAS SHUT DOWN IN FLIGHT.  THE AIRCAFT DIVERTED FOR AN UNSCHEDULED LANDING.  P&WC WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRCT00012WIE35NE                
20060615002042006061500204NE  2006       6          15         CA060228018      220060206G7314B8187B          PUMP                                    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              FUEL SYSTEM     SEIZED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      CA       628                                                            PILOT WAS ATTEMPTING TO START THE AIRCRAFT AND THE AUX PUMP LIGHT ILLUMINATED AND THE CB POPPED.  IT WAS RESET AND AGAIN THE CB POPPED.  THE PUMP WAS REPLACED AND NO FURTHER DEFECT WAS NOTED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1G71 3O3  O  H11NM   1E4                  
20060616000382006061600038NE  2006       6          16         CA060228019      220060220G7314B8187B          PUMP                                    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              FUEL            FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       128                                                            DURING START UP PILOT COULD NOT PRIME THE AIRCRAFT.  FURTHER INVESTIGATION FOUND PUMP FAILED.  PUMP REPLACED AND NO FURTHER DEFECTS NOTED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3O3  O  H11NM   1E4                  
20060616000402006061600040    2006       6          16         CA060228021      420060210G2562PS400010        ELT                                     ROBSINR44   R44         7640120WP  LYC   O540  O540F1B5    41532EA                              CABIN           MALFUNCTIONED   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            93                                                        DURING AN ANNUAL ELT RECERTIFICATION A FUNCTION CHECK OF THE G SWITCH WAS CARRIED OUT.  IT WAS NOTED TO SET OFF PRIOR TO ITS REQUIRED SETTING (FAULTY G SWITCH).  ELT HAS BEEN SENT BACK TO POINTER FOR REPAIR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1G71 3O3  O  H11NM   E295                 
20060616000432006061600043NM  2006       6          16         CA060301002      120060227G324026124121A       CARRIER ASSY                            BOEING767   7673Y0             NM  PWA   4060  PW4060      52119NE                              NR 4 BRAKE      BURNED          W      O   OTHER                                                                                           A  FLAME/FIRE                                                                    TXTAXI/GRND HDL  1                      CA                                                                      GND CREW REPORTED BRAKE FIRE ON RT MAIN GEAR AFTER SHUTDOWN.  FIRE EXTINGUISHED.  FOUND NR 4 BRAKE PISTONS WORN THROUGH STATORS AND INTO THE ROTORS.  AXLE INSPECTED AS PER AMM 05-51-15-212-001 AND 05-51-14 PB201.  AXLE OK.  BRAKE REPLACED AS PER JC 6-232A.  WHEEL ASSY.  REPLACED AS PER JC 6-232B.  FURTHER INFO WILL FOLLOW WITH WHEEL/BRAKE SHOP REPORT.                                                                                                                                                                                                                                                                                                                                                                               2L72 4F4  FRTA1NM    E24NE                
20060616000442006061600044    2006       6          16         CA060301003      420060301G2562PS400010        ELT                                     ROBSINR44   R44         7640120WP  LYC   O540  O540F1B5    41532EA                              CABIN           WEAK            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            657                                                       DURING ANNUAL RECERTIFICATION, FOUND G SWITCH WEAK.  ELT SENT BACK TO OVERHAUL FACILITY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1G71 3O3  O  H11NM   E295                 
20060616000452006061600045    2006       6          16         CA060301004      420060301G2562PS400010        ELT                                     ROBSINR44   R44         7640120WP  LYC   O540  O540F1B5    41532EA                              CABIN           WEAK            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            92                                                        DURING ANNUAL RECERTIFICATION, FOUND G SWITCH WEAK.  ELT SENT BACK TO OVERHAUL FACILITY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1G71 3O3  O  H11NM   E295                 
20060616000472006061600047EA  2006       6          16         CA060301005      120060228G541060L12AA         COWL LATCH                              DHAV  DHC2  DHC2MK3     2800107EA                                                               NACELLE         DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      INSPECTION PERSONNEL AT VIKING AIR HAVE DISCOVERED A REOCCURENCE OF SUBSTANDARD COWL LATCHES; THIS ISSUE WAS PREVIOUSLY RAISED, AND ADDRESSED THROUGH 2 SERVICE BULLETINS, TB/7 (FOR THE TURBO BEAVER) AND 6/34 (FOR THE TWIN OTTER).                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1H71 3T      A806                         
20060616000482006061600048EA  2006       6          16         CA060301006      120060228G541060L12AA         COWL LATCH                              DHAV  DHC6  DHC6        2802606EA                                                               NACELLE         DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      INSPECTION PERSONNEL AT VIKING AIR HAVE DISCOVERED A REOCCURRENCE OF SUBSTANDARD COWL LATCHES; THIS ISSUE WAS PREVIOUSLY RAISED, AND ADDRESSED THROUGH 2 SERVICE BULLETINS - TB/7 (FOR THE TURBO BEAVER) AND 6/34 (FOR THE TWIN OTTER).                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1H72 3T    RTA9EA                         
20060616000492006061600049CE  2006       6          16         CA060301007      120060224G3230K10004          NUT PLATE       BEECH       1018200351  BEECH B300  B300        1159232CE  PWA   PT6   PT6A60A     52043NE  HARTZLHCB4M HCB4M       GL  MLG             DAMAGED         W      L   ABORTED APPROACH                                                                                N  FALSE WARNING                                                                 APAPPROACH       1                      CA       1700       PAC16505                                            AIRCRAFT WAS ON APPROACH.  POSITIVE NOSE GEAR DOWN LOCK WAS NOT INDICATING USING THE NORMAL SYSTEM.  EMERGENCY GEAR DOWN WAS REQUIRED TO HAVE POSITIVE DOWN AND LOCK INDICATION.  NOSE LANDING GEAR INSPECTION WAS CARRIED OUT OF THE GREEN LIGHT INDICATOR SWITCHES ON THE ACTUATOR AND DRAG BRACE.  THE SWITCH STOP WAS BACKED OFF INTO THE ANCHOR NUT.  STOP WAS RERIGGED AND SECURED.  LANDING GEAR SWING CARRIED OUT AS PER B300 MM AND CHECKED SERVICEABLE.                                                                                                                                                                                                                                                                               2L72 4T4  TRTA24CE   E4EA    6  CP56GL    
20060616001092006061600109NM  2006       6          16         CA060302001      120060227G2121                BEARING         SUNDSTRANDAI            BOEING767   767300      1385204NM  GE    CF6   CF680C2B7        NE                              COOLING FAN     DAMAGED         W      H   DEACTIVATE SYST/CIRCUITS                                                                        B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA            8132  3490                                                FORWARD EQUIPMENT COOLING FAN BEARINGS APPEARED TO BE DAMAGED AND THE FAN SHOWS SIGNS OF RUBBING ON THE CASE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  FRTA1NM    E13NE                
20060619000462006061900046EA  2006       6          19         CA060302002      120060223G2810215640011       FUEL CELL                               CNDAIRCL215 CL2156B11215       EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  NR 1            LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       1253                                                           WHILE COMPLETING THE A 500 HR INSPECTION, FUEL WAS FOUND DRIPPING FROM THE RIGHT WING TIP.  BY TRANSFERRING FUEL IT WAS DETERMINED THAT THE LEAK WAS IN THE RIGHT FUEL SYSTEM.  THE A/C WAS DEFUELED AND THE FUEL CELLS WERE TAKEN OUT AND CHECKED FOR LEAKS.  UPON INSPECTION 6 OUT OF THE 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE.  CELL WAS REMOVED AND REPLACED.                                                                                                                                                                                                                                                                                                                                                                2H72 4T4  TRTA14EA   E20NE   6  CP7NE     
20060619000472006061900047EA  2006       6          19         CA060302003      120060223G281021564002        FUEL CELL                               CNDAIRCL215 CL2156B11215       EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  NR 2            LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       1253                                                           WHILE COMPLETING THE A 500 HR INSPECTION FUEL WAS FOUND DRIPPING FROM THE RIGHT WING TIP.  BY TRANSFERING FUEL IT WAS DETERMINED THAT THE LEAK WAS IN THE RIGHT HAND FUEL SYSTEM.  THE A/C WAS DEFUELED AND THE FUEL CELLS WERE TAKEN OUT AND CHECKED FOR LEAKS.  UPON INSPECTION 6 OUT OF THE 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE.                                                                                                                                                                                                                                                                                                                                                                                             2H72 4T4  TRTA14EA   E20NE   6  CP7NE     
20060619000482006061900048EA  2006       6          19         CA060302004      120060223G2810215640024       FUEL CELL                               CNDAIRCL215 CL2156B11215       EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  NR 3            LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       1253                                                           WHILE COMPLETING THE A 500 HR INSPECTION FUEL WAS FOUND DRIPPING FROM THE RIGHT WING TIP.  BY TRANSFERING FUEL IT WAS DETERMINED THAT THE LEAK WAS IN THE RIGHT HAND FUEL SYSTEM.  THE A/C WAS DEFUELED AND THE FUEL CELLS WERE TAKEN OUT AND CHECKED FOR LEAKS.  UPON INSPECTION 6 OUT OF THE 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE.  CELL WAS REMOVED AND REPLACED.                                                                                                                                                                                                                                                                                                                                                             2H72 4T4  TRTA14EA   E20NE   6  CP7NE     
20060619000492006061900049EA  2006       6          19         CA060302005      120060223G2810215640026       FUEL CELL                               CNDAIRCL215 CL2156B11215       EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  NR 5            LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       1253                                                           WHILE COMPLETING THE A 500 HR INSPECTION FUEL WAS FOUND DRIPPING FROM THE RIGHT WING TIP.  BY TRANSFERRING FUEL IT WAS DETERMINED THAT THE LEAK WAS IN THE RIGHT HAND FUEL SYSTEM.  THE A/C WAS DEFUELED AND THE FUEL CELLS WERE TAKEN OUT AND CHECKED FOR LEAKS.  UPON INSPECTION 6 OUT OF THE 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE.  CELL WAS REMOVED AND REPLACED.                                                                                                                                                                                                                                                                                                                                                            2H72 4T4  TRTA14EA   E20NE   6  CP7NE     
20060619000502006061900050EA  2006       6          19         CA060302006      120060223G281021564002        FUEL CELL                               CNDAIRCL215 CL2156B11215       EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  NR 6            LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       1253                                                           WHILE COMPLETING THE A 500 HR INSPECTION, FUEL WAS FOUND DRIPPING FROM THE RIGHT WING TIP.  BY TRANSFERING FUEL IT WAS DETERMINED THAT THE LEAK WAS IN THE RIGHT HAND FUEL SYSTEM.  THE A/C WAS DEFUELED AND THE FUEL CELLS WERE TAKEN OUT AND CHECKED FOR LEAKS.  UPON INSPECTION 6 OUT OF THE 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE.  CELL WAS REMOVED AND REPLACED.                                                                                                                                                                                                                                                                                                                                                            2H72 4T4  TRTA14EA   E20NE   6  CP7NE     
20060619000512006061900051EA  2006       6          19         CA060302007      120060223G2810215640751       FUEL CELL                               CNDAIRCL215 CL2156B11215       EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  NR 8            LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       1253                                                           WHILE COMPLETING THE A 500 HR INSPECTION FUEL WAS FOUND DRIPPING FROM THE RIGHT WING TIP.  BY TRANSFERRING FUEL IT WAS DETERMINED THAT THE LEAK WAS IN THE RIGHT HAND FUEL SYSTEM.  THE A/C WAS DEFUELED AND THE FUEL CELLS WERE TAKEN OUT AND CHECKED FOR LEAKS.  UPON INSPECTION 6 OUT OF THE 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE.  CELL WAS REMOVED AND REPLACED.                                                                                                                                                                                                                                                                                                                                                            2H72 4T4  TRTA14EA   E20NE   6  CP7NE     
20060616001462006061600146EA  2006       6          16         CA060302008      120060223G2810CL215640751     FUEL CELL                               CNDAIRCL215 CL2156B11215       EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE                  LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       1342                                                           WHILE COMPLETING THE A 500 HR INSPECTION FUEL WAS FOUND DRIPPING FROM THE RIGHT WING TIP.  BY TRANSFERRING FUEL IT WAS DETERMINED THAT THE LEAK WAS IN THE RIGHT FUEL SYSTEM.  THE A/C WAS DEFUELED AND THE FUEL CELLS WERE TAKEN OUT AND CHECKED FOR LEAKS.  UPON INSPECTION 6 OUT OF THE 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE.  CELL WAS REMOVED AND REPLACED.                                                                                                                                                                                                                                                                                                                                                                 2H72 4T4  TRTA14EA   E20NE   6  CP7NE     
20060616001472006061600147WP  2006       6          16         CA060302009      120060220G2913                SEAL            ROBSIN                  ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              HYDRAULIC PUMP  LEAKING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1664       0763                                                INPUT SEALS FOUND TO BE LEAKING DURING INSPECTION.  PUMP WAS REPLACED WITH SERVICEABLE UNIT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1G71 3O3  O  H11NM   1E4                  
20060616001482006061600148WP  2006       6          16         CA060302010      120060220G6730                SEAL                                    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              SERVO           LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       1664                                                           LOWER PISTON SEAL WAS FOUND LEAKING.  SERVO WAS REPLACED WITH A SERVICEABLE UNIT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1G71 3O3  O  H11NM   1E4                  
20060616001492006061600149WP  2006       6          16         CA060302011      120060220G6730VARIOUS         SEAL            ROBSIN                  ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              SERVO           LEAKING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1664       1976                                                UPPER PISTON SEAL LEAKING.  NEW SEAL AND O-RING INSTALLED.  NO FURTHER DEFECTS FOUND.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1G71 3O3  O  H11NM   1E4                  
20060619002522006061900252GL  2006       6          19         CA060302012      220060118G7297                WIRE HARNESS                            CVAC  440   440         2422902WP  ALLSN 501D  501D13      03004GL                              LT ENGINE       MISINSTALLED    W      E   ENGINE SHUTDOWN                                                                                 O  OTHER                                                                         CRCRUISE         1                      CA                                                                      AIRCRAFT ON A TEST FLIGHT AND DURING AN RPM DECAY TEST, THE LT ENGINE POWER LEVER WAS REDUCED BELOW 1400 HP.  THE RPM THEN STARTED TO DECAY BELOW PRESCRIBED LIMITS.  DUE TO THIS, THE CREW ELECTED TO SHUT DOWN THE ENGINE.  THE PROBLEM ONLY OCCURRED BELOW 1400 HP.  THE CREW CARRIED OUT SEVERAL RESTARTS, WHICH DID NOT RESOLVE THE OCCURRENCE AND ELECTED TO LAND WITH THE ENGINE SHUT DOWN.  TROUBLE SHOOTING IDENTIFIED AN INCORRECT WIRING CONFIGURATION, WHICH WAS CORRECTED.                                                                                                                                                                                                                                                         2L72 4R4  T  6A6     E282                 
20060619000812006061900081EA  2006       6          19         CA060302013      120060226G5610NP1393226       WINDOW                                  CNDAIRCL600 CL6002C10   1390015EA  GE    CF34  CF348C1          NE                              COCKPIT         CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         APAPPROACH       1                      CA       6762                                                           COPILOT SIDE WINDOW BROKEN.  SIDE WINDOW CHECKED, FOUND MIDDLE PLY DAMAGED.  RT SIDE WINDOW ACC AMM TASK 56-12-01-000-801 CHANGED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F4  FRTA21EA   EOOO63EN             
20060619000892006061900089EA  2006       6          19         CA060302014      120060228G2133GG670980041     OUTFLOW VALVE                           CNDAIRCL600 CL6002C10   1390015EA  GE    CF34  CF348C1          NE                              CABIN PRESSURE  MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      UNABLE TO PRESSURIZE CABIN IN FLIGHT.  AIRCRAFT RETURNEDTO FIELD OF ORIGIN.  GROUND VALVE REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F4  FRTA21EA   EOOO63EN             
20060619000912006061900091WP  2006       6          19         CA060303001      120060301G2822B8187B          PUMP                                    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              FUEL SYS        FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA       541                                                            DURING START UP THE AUX FUEL PUMP C/B POPPED.  FUEL PUMP WAS REPLACED AND NO FURTHER DEFECTS WERE NOTED.  HAVE AUDITED THE FUEL PUMP ISSUE.  HAVE HAD SEVERAL PUMPS IN THE LAST YEAR FAIL.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3O3  O  H11NM   1E4                  
20060619000932006061900093CE  2006       6          19         CA060303002      120060201G571118144L          SPAR                                    BEECH 18    3TM         1151046CE  PWA   R985  R985AN14B   52008NE  HAMSTD22D   22D30       NE  WING            CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       8290                                                           CENTER SECTION FUSELAGE REAR WING CARRY-THRU SPAR CRACKED 3/4" FROM TOP OF SPAR RUNNING DOWNWARD AT EDGE OF REINFORCEMENT INSIDE FUSELAGE AT REAR LT FLOAT FITTING STATION NR 199.5 BULKHEAD NR 8.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L72 3R3  R  A765    5E1     5  CP736     
20060619000962006061900096    2006       6          19         CA060303003      420060221G3497                CONNECTOR       COLLINS     6227384001  CNDAIRCL600 CL600*             EA  GE    CF34  CF34*            NE                              ANTENNA         CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1325 1325  1WGNF                                               WHILE TROUBLESHOOTING A DEFERRAL FOR AN ADF SIGNIFICANT CORROSION AND A BROKEN PIN WAS DISCOVERED ON THE BELLY MOUNTED ADF ANTENNA CONNECTOR.  THE ASSOCIATED CONNECTOR WAS ALSO CORRODED AND CONTAINED THE BROKEN PIN.  IT IS ASSUMED MOISTURE FROM THE AIRCRAFT INTERIOR FOUND ITS WAY INTO THE CONNECTOR AND POOLED CAUSING THE CORROSION.  THE ANTENNA SEALS AERODYNAMIC AND PRESSURE WERE IN A SERVICABLE STATE.  MAINTENANCE REPLACED THE ADF ANTENNNA, CONNNECTOR PLUG AND PINS AND RETURNED THE AIRCRAFT TO SERVICE.                                                                                                                                                                                                                    2L72 4F4  FRTA21EA   E15NE                
20060619000982006061900098CE  2006       6          19         CA060303005      120060116G2821305262401       FILTER                                  CESSNA500   560CESSNA   2076750CE  PWA   530   PW535A           NE                              RT FUEL SYS     CONTAMINATED    W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1148                                                           RT ENGINE FUEL FILTER CONTAMINATED WITH LINT FROM LARGE (12" X 30") TOWEL WHICH WAS FOUND IN THE RT INTEGRAL WING TANK.  THE TOWEL WAS "INSTALLED" BY CESSNA AIRCRAFT FACTORY WHEN THE AIRCRAFT WAS BUILT.  THE TOWEL WAS OUTBOARD OF THE BOOST AND EJECTOR PUMPS AND DID NOT AFFECT THE OPERATION OF ENGINE OR PUMPS.                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA22CE   E00053EN             
20060619000992006061900099CE  2006       6          19         CA060303006      120060116G2710556555038CR     CONTROL CABLE                           CESSNA500   560CESSNA   2076750CE  PWA   530   PW535A           NE                              AILERON         BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1148                                                           RT AILERON CONTROL YOKE CROSSOVER CABLE BROKEN STRANDS.  THIS WAS FOUND ON PHASE 5 INSPECTION AND IS A COMMON FINDING AT 1200 HOURS OF USE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA22CE   E00053EN             
20060619001002006061900100CE  2006       6          19         CA060303007      120060116G2710656512037CR     CONTROL CABLE                           CESSNA500   560CESSNA   2076750CE  PWA   530   PW535A           NE                              AILERONS        BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1148                                                           LT AILERON CONTROL YOKE CROSSOVER CABLE BROKEN STRANDS.  THIS WAS FOUND AT PHASE 5 INSPECTION AND IS A COMMON FINDING AT 1200 HOURS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F4  FRTA22CE   E00053EN             
20060619001012006061900101CE  2006       6          19         CA060303008      120060116G5220651126619       SEAL            CESSNA                  CESSNA500   560CESSNA   2076750CE  PWA   530   PW535A           NE                              ESCAPE HATCH    FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1148                                                           ESCAPE HATCH SEAL MIGRATING UNDER CABIN PRESSURE TO THE EXTERIOR OF THE AIRCRAFT.  DUE TO POOR BONDING TO THE HATCH STRUCTURE.  REPLACED SEAL AND PRESSURIZED AIRCRAFT, SERVICEABLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F4  FRTA22CE   E00053EN             
20060619001022006061900102CE  2006       6          19         CA060303009      120060116G32440316138         TIRE                                    CESSNA500   560CESSNA   2076750CE  PWA   530   PW535A           NE                              NLG             SEPARATED       W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       678                                                            NOSE WHEEL TIRE, TREAD IS STARTING TO SEPARATE FROM TIRE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F4  FRTA22CE   E00053EN             
20060619002792006061900279SW  2006       6          19         CA060303010      120060303G3240                HOSE                                    AIRTRCAT802 AT802A      0390308SW  PWA   PT6   PT6A67A     52043NE  HARTZLHCB5M HCB5MA3     GL  BRAKE           CHAFED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       303                                                            WHILE PERFORMING A GEAR SWING DURING THE ANNUAL INSPECTION, IT WAS DISCOVERED THAT THE MLG BRAKE HOSES WERE ROUTED SO THAT THEY WERE RUBBING DIRECTLY ON THE TREAD PORTION OF THE TIRES.  THE STRAIGHT BULKHEAD FITTINGS P/N AN832-4D (4 OF) WERE REPLACED WITH 45 DEGREE BULKHEAD FITTINGS AND BRAKE HOSES WERE CHECKED FOR CLEARANCE ON A SUBSEQUENT GEAR SWING WITH NO RUBBING NOTED.  BRAKE SYSTEM WAS BLED.  THE OTHER AIRCRAFT IN THE FLEET WILL BE INSPECTED.                                                                                                                                                                                                                                                                            1L71 3T4  TNCA19SW   E26NE   6  CP44GL    
20060621000682006062100068CE  2006       6          21         CA060303011      120060204G21607547512         BYPASS VALVE    HAMSTD      73838426    CESSNA500   560CESSNA   2076750CE  PWA   530   PW535A           NE                              ACM             FAILED          W      O   OTHER                                                                                           MP OVER TEMP                 NO WARNING INDICATION                               CRCRUISE         1                      CA       1189       200303012                                           BYPASS VALVE INTERMITTENTLY STICKING IN OPEN (HOT) POSITION, UNABLE TO CONTROL CABIN AIR TEMPERATURE IN AUTO OR MANUAL SELECTION.  REPLACED VALVE, GROUND CHECK OF VALVE OPERATION SATISFACTORY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F4  FRTA22CE   E00053EN             
20060621000692006062100069CE  2006       6          21         CA060303012      120060210G2916S53FC           GAUGE           CESSNA      651710021   CESSNA500   560CESSNA   2076750CE  PWA   530   PW535A           NE                              RESERVOIR       FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       1204                                                           BRAKE HYDRAULIC RESERVOIR UPPER AND LOWER SIGHT GAGES UNSERVICEABLE, SIGHT GAGE FLOATS ABSORBED SKYDROL BRAKE FLUID AND WOULD NOT FLOAT, MAKING IT IMPOSSIBLE FOR THE (PILOT) TO DETERMINE THE BRAKE FLUID LEVEL.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F4  FRTA22CE   E00053EN             
20060621000702006062100070CE  2006       6          21         CA060303013      120060211G27520523921         ROLLER          CESSNA                  CESSNA172   172M        2072418CE  LYC   O320  O320E2D     41508EA  MCAULY1C160 1C160DTM    GL  TE FLAP         MISSING         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      12 HOURS AFTER THE AIRCRAFT CAME BACK FROM A PAINT JOB, A FLIGHT INSTRUCTOR HEARD A BANG AS THEY WERE RETRACTING THE FLAPS AFTER LANDING.  AFTER TAXIING BACK TO THE HANGAR, AND UPON SUBSEQUENT INSPECTION, OUR FLIGHT INSTRUCTOR REPORTED THE LT IB AFT FLAP ROLLER MISSING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H71 3O3  ONT3A12    E274    5  NP910     
20060621000712006062100071CE  2006       6          21         CA060303014      120060131G2720                STOP FITTING                            CESSNA150   150F        2071814CE  CONT  O200  O200A       17020SO  MCAULY1A100 1A100MCM    GL  RUDDER          FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      SDA AL-2000-04 CF-2000-20R2 SEB 01-1 COMPLETED, NO EVIDENCE OF JAMMING OR RUBBING ON EITHER RUDDER STOPS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3O3  O  3A19    E252    5  NP918     
20060621000752006062100075EA  2006       6          21         CA060303019      120060303G2810CL21564002      FUEL CELL                               CNDAIRCL215 CL2156B11215       EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  RT NR 6         LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       1342                                                           WHILE UNDERGOING IT'S 12 MTH INSPECTION FUEL WAS FOUND DRIPPING FROM THE RT WING TIP.  ALL 8 FUEL CELLS FROM THE RT WING WERE REMOVED FOR LEAK CHECK.  6 OUT OF 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE.  DEFECTIVE CELLS WILL BE REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2H72 4T4  TRTA14EA   E20NE   6  CP7NE     
20060622000712006062200071EA  2006       6          22         CA060303020      120060303G2810CL215640026     FUEL CELL                               CNDAIRCL215 CL2156B11215       EA  PWA   PW120 PW123            NE                              RT WING         LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       1342                                                           WHILE UNDERGOING IT'S 12 MTH INSPECTION FUEL WAS FOUND DRIPPING FROM THE RIGHT WING TIP.  ALL 8 FUEL CELLS FROM THE RIGHT WING WERE REMOVED FOR LEAK CHECK. 6 OUT OF 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE.  DEFECTIVE CELLS WILL BE REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2H72 4T4  TRTA14EA   E20NE                
20060621001332006062100133EA  2006       6          21         CA060303021      120060303G2810CL215640024     FUEL CELL                               CNDAIRCL215 CL2156B11215       EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  RT NR 3         LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       1342                                                           (CAN) WHILE UNDERGOING 12 MONTH INSPECTION, FUEL WAS FOUND DRIPPING FROM THE RT WING TIP.  ALL 8 FUEL CELLS FROM THE RT WING WERE REMOVED FOR LEAK CHECK.  6 OUT OF 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE. DEFECTIVE CELLS WILL BE REPLACED. (TC NR 20060303021)                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2H72 4T4  TRTA14EA   E20NE   6  CP7NE     
20060621001342006062100134EA  2006       6          21         CA060303022      120060303G2810CL21564002      FUEL CELL                               CNDAIRCL215 CL2156B11215       EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  RT NR 2         LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       1342                                                           (CAN) WHILE UNDERGOING 12 MONTH INSPECTION, FUEL WAS FOUND DRIPPING FROM THE RT WING TIP.  ALL 8 FUEL CELLS FROM THE RT WING WERE REMOVED FOR LEAK CHECK. 6 OUT OF 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE. DEFECTIVE CELLS WILL BE REPLACED. (TC NR 20060303022)                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2H72 4T4  TRTA14EA   E20NE   6  CP7NE     
20060621001352006062100135EA  2006       6          21         CA060303023      120060303G2810CL215640011     FUEL CELL                               CNDAIRCL215 CL2156B11215       EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  RT NR 1         LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       1342                                                           (CAN) WHILE UNDERGOING 12 MONTH INSPECTION, FUEL WAS FOUND DRIPPING FROM THE RT WING TIP. ALL 8 FUEL CELLS FROM THE RT WING WERE REMOVED FOR LEAK CHECK. 6 OUT OF 8 CELLS WERE FOUND TO BE LEAKING INCLUDING THIS ONE. DEFECTIVE CELLS WILL BE REPLACED. (TC NR 20060303023)                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2H72 4T4  TRTA14EA   E20NE   6  CP7NE     
20060621001392006062100139WP  2006       6          21         CA060306004      120060228G2740T40032          TRIM SWITCH                             ROBSINR44   R44         7640120WP  LYC   O540  O540F1B5    41532EA                                              FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN)  TRIM SWITCH INTERMITTENT.   REPLACED SWITCH.  (TC NR 20060306004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1G71 3O3  O  H11NM   E295                 
20060621001402006062100140EU  2006       6          21         CA060306005      120060106G6720350A33105803    CONTROL LEVER                           SNIAS 350   AS350*             EU  TMECA ARRIELARRIEL1B    6OO30NE                              T/R GEARBOX     WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN)  CONTROL TUBE WORN IN ATTACH POINT OF CONTROL LEVER.   REPLACED LEVER.  (TC NRV 20060306005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1G71 3U3  U  H9EU    E19EU                
20060623000342006062300034EA  2006       6          23         CA060306006      220060306G7250311532101       TURBINE BLADES                                                             PWA   PT6T  PT6T3       52045EA                              POWER SECTION   DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       148213641                                                      (CAN) POWER SECTION WAS RECEIVED FROM THE OPERATOR FOR REPAIR DUE TO HIGH VIBRATION LEVELS.  INSPECTION REVEALED THAT THE COMPRESSOR TURBINE BLADES HAD SUFFERED EXTENSIVE DAMAGE. 12 CT BLADES WERE FOUND DAMAGED TO VARYING DEGREES OF THE BLADE SURFACE MISSING. ANOTHER 12 BLADES EXHIBITED FATIGUE CRACKING EMANATING FROM THE TRAILING EDGE OF THE BLADE.  (TC NR 20060306006)                                                                                                                                                                                                                                                                                                                                                                   4  U          E22EA                
20060623001602006062300160EA  2006       6          23         CA060306007      220060110G74144347            MAGNETO                                 HUGHES269   269C1       8059504SW  LYC   O360  HO360C1A    41514EA                              ENGINE          FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            1793                                                      (CAN)  AIRCRAFT HARD TO START AND 125 DROOP.  REPLACED LT MAGNETO.  (TC NR 20060306007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1G71 3O3  OO 4H12    E286                 
20060623001632006062300163EA  2006       6          23         CA060306008      220060112G7322252434710       FUEL CONTROL                            SCWZER269   269D        8059501EA  LYC   O360  HIO360D1A   41514EA                              ENGINE          MALFUNCTIONED   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       500        73707                                               (CAN) CANNOT UNJUST IDLE MIXTURE.  REPLACED FUEL CONTROL.  (TC NR 20060306008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1G71 3U3  O0 4H12    1E10                 
20060623001692006062300169SW  2006       6          23         CA060306013      120060113G801131B21064        STARTER                                 HUGHES269   269C1       8059504SW  LYC   O360  HO360C1A    41514EA                              ENGINE          FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            61                                                        (CAN)  STARTER NOT OPERATING.  REPLACED STARTER.  (TC NR 20060306013)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1G71 3O3  OO 4H12    E286                 
20060623002252006062300225    2006       6          23         CA060306017      420060303G25654A40302         SLIDE                                   EMB   ERJ170ERJ170100LR        EU  GE    CF34  CF348E5A1   30015NE                              L1 DOOR         FAULTY          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       792                                                            (CAN) IAW FLEET ENGINEEERING REQUEST VERIFY  L-1, R-1, L-2 AND R-2 SLIDE FOR ANY EXTRA LACING AROUND THE SLIDE PACK OPENING PIN. CONTACT MOC FOR INSTRUCTIONS AND PHOTOS OF PROPER INSTALLATION . REPORT FINDING FOR EACH DOOR AND CORRECTIVE ACTION IF REQUIRE.  L1 DOOR SLIDE ASSEMBLY REPLACED IAW AMM,NEW SLIDE ASSY INSTALLED IAW AMM. (TC NR 20060306017)                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA56NM   E00063EN             
20060623002282006062300228CE  2006       6          23         CA060306018      120060303G3710AA216CWOHE      PUMP                                    CESSNA206   U206G       2073356CE  CONT  O520  IO520F      17032SO  HARTZLHCC3Y PHCC3YF1    GL  AIR PUMP        FAILED          W      A   UNSCHED LANDING                                                                                 L  NO TEST                                                                       CRCRUISE         1                      CA            144                                                       (CAN) AIR PUMP WAS INSTALLED IN AIRCRAFT AND FAILED AFTER 144 HOURS. (TC NR 20060306018)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1H71 3O3  O  A4CE    E5CE    5  CP25EA    
20060623002292006062300229CE  2006       6          23         CA060306019      120060304G3710AA216CWOHE      PUMP                                    CESSNA206   U206G       2073356CE  CONT  O520  IO520F      17032SO  HARTZLHCC3Y PHCC3YF1    GL  AIR PUMP        FAILED          W      E   ENGINE SHUTDOWN                                                                                 O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA            1                                                         (CAN) AIR PUMP WAS INSTALLED IN AIRCRAFT AND FAILED AFTER 0.7 HOURS, FAILED DURING THE RUN UP. (TC NR 20060306019)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O3  O  A4CE    E5CE    5  CP25EA    
20060626000562006062600056EU  2006       6          26         CA060306020      120060304G2750MS24178D1       RELAY                                   DORNERDO228 DO228202    2992030EU  GARRTTTPE331TPE3315251K      NM  HARTZLHCB4T HCB4TN5     GL  TE FLAPS        INOPERATIVE     W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA                                                                      (CAN) ON APROACH FLAPS WERE SELECTED TO THE NR 2 POSITION AND DID NOT RESPOND . SYSTEM TROUBLESHOOTING FOUND THE RELAY TO BE NOT FUNCTIONING . RELAY WAS REPLACED WITH A SERVICABLE UNIT AND FLAPS TESTED NORMAL (TC NR 20060306020)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2H72 4T4  TRTA16EU   E2WE    6  CP40EA    
20060703000022006070300002    2006       7          3          CA060307001      420060304G34606224717004      CONTROL PANEL                           BOEING767   767375      1385217NM  GE    CF6   CF680C2B6F  30025NE                              COCKPIT         MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 F  FLT CONT AFFECTED                                                             CLCLIMB          1                      CA                                                                      ON CLIMB-OUT YVR, NO A/T, NO CMD BARS, NO A/P L AND C. NO L NAV, (ACFT RETURNED TO YVR).  REPLACED MCP PER AMM 22-11-02 PB 201.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA1NM    E13NE                
20060626000572006062600057    2006       6          26         CA060307002      420060305G34449733033111      PROXIMITY SWITCH                        PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL                  FAULTY          W      O   OTHER                                                                                           N  FALSE WARNING                                                                 CRCRUISE         1                      CA       5497                                                           (CAN) DURING CRUISE, THE (AIR/GROUND) LIGHT ON THE CAWS PANEL ILLUMINATED. UPON TOUCHDOWN, THE LIGHT WENT OUT.  INVESTIGATION REVEALED A FAULTY LT GROUND PROXIMITY SWITCH. THE SWITCH WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20060307002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20060626000582006062600058    2006       6          26         CA060307003      420060125G221611538011119     ACCUMULATOR     BEECH                   BEECH 100   A100        1152915CE  PWA   PT6   PT6A28           EA  HARTZLHCB3T HCB3TN3     GL  HORIZONTAL STAB FAILED          W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             CRCRUISE         1                      CA                                                                      (CAN) THE ABOVE P/N FAILED SENT FOR REPAIR THEN FAILED AGAIN WITH IN 5.3 HRS. SERVICEABLE ACTUATOR INSTALLED WITH NO MORE PROBLEMS. (TC NR 20060307003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L72 3T4  T  A14CE   E4EA    6  CP15EA    
20060626000592006062600059NE  2006       6          26         CA060307004      220060303G7210MS949034        BOLT            PWA         PT6A65AR                                       PWA   PT6   PT6A65AR    52043NE                              GEARBOX         FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       20   20    PCEPS97533                                          (CAN) THE POWER SECTION OF ENGINE S/N PCE-PS 97533 WAS REMOVED DUE TO SEIZED CONDITION. THE REASON FOR REMOVAL AS DESCRIBED BY THE OPERATOR WAS FAILURE ON START-UP. THE POWER SECTION ROTATION HUNG ON LIGHT UP, RELEASED AND HUNG UP AGAIN.  START ABORTED.  POWER SECTION BINDS UP DURING MANUAL ROTATION. (TC NR 20060307004)                                                                                                                                                                                                                                                                                                                                                                                                                      4  T          E4EA                 
20060626000602006062600060CE  2006       6          26         CA060307005      120060106G32301280811         MOTOR                                   CESSNA210   210         2073402CE                                                               MLG             ERRATIC         W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA       721                                                            (CAN) GEAR MOTOR CHANGED DUE TO ERATIC GEAR OPERATION.  GEAR MOTOR WAS SPRAYING SOLDER.  PRESSURE SWITCH ADJUSTED TO SPEC FOR GEAR OPEARTION.  (TC NR 20060307005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O    RT3A21                         
20060626000612006062600061GL  2006       6          26         CA060307006      120060303G2720C2CF177A        MOUNT                                   DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE  HAMSTD2D    2D30        NE  RUDDER PEDALS   CRACKED         W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             LDLANDING        1                      CA                                                                      (CAN) UPON LANDING, PILOT NOTICED THAT RUDDER PEDALS FELT LOOSE.  HAD NO PROBLEM WITH TAXING AND ON THE WATER. AC WAS REMOVED FROM SERVICE, INSP CARRIED OUT. CABLES WERE FOUND TO BE LOOSE. BELLY PNLS WHERE REMOVED, RUDDER BAR ASSY WAS INSPECTED. IT WAS NOTICED THAT RUDDER TUBES ON LT SIDE WERE RUBBING TOGETHER. UPON FURTHER VISUAL INSP IT WAS NOTICED THAT MOUNT ASSY P/N C2CF177A WAS PULLED AWAY FROM ITS SUPPORT TUBE. WELD THAT SECURES IT TO TUBE HAD FAILED WHICH CAUSED STRESS ON OTHER SUPPORT TUBE, CAUSED MOUNT ASSY TO CRACK, COME AWAY FROM TUBE WHICH IN TURN CAUSED SLACK IN CABLES. RUDDER BAR WAS REMOVED FROM AC, PICTURES TAKEN, BAR WAS SENT FOR REPAIRS AS NO SPARE ASSY WAS AVAILABLE. (TC NR 20060307006)      1H71 3R3  RRCA806    5E1     5  CP206     
20060626000622006062600062EU  2006       6          26         CA060307007      120060302G750026361090018     BLEED AIR SYS                           AIRBUSA319  A319112     3930323EU  CFMINTCFM565CFM565B6    13802NE                              NR 2            INOPERATIVE     W      B   EMER. DESCENT                                                                                   J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN)  DISPATCHED WITH BLEED NR 2 OFF IAW MEL.  LT WING LEAK IN CRUISE EMERGENCY DESCENT COMPLETED.  REMOVED ACCESS PANELS FOR  ZONE 521 BLEED DUCT FROM THE ENG NR 1 PYLON TO THE FUSELAGE. REMOVED ACCESS DOORS TO AIR CONDITIONING UNITS (191+192). REMOVED BELLY FAIRINGS FOR ACCESS TO BLEED DUCT FWD OF THE AIR CONDITIONING UNITS. (TC NR 20060307007)                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  FRTA28NM   E37NE                
20060626000662006062600066NE  2006       6          26         CA060307008      220060306G7230                VANE                                    AIRBUS320   A320211     3930320EU  CFMINTCFM56 CFM565A1         NE                              3RD STAGE VSV   CHAFED          W      B   EMER. DESCENT                                                                                   O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) NR 1 ENG STALL, ENG 1 SHUTDOWN AND LANDED.  BORESCOPE CARRIED OUT IAW AMM 72-00-00-200-003 AND 72-31-00-290-001 FOUND 3 RD STAGE VSV  VANES RUBBING ON IB END MAKEING A GROOVE WITH DISPLACED METAL AT BOTH ENDS OF VANE TRAVEL. (TC NR 20060307008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F4  FRTA28NM   E29NE                
20060703000062006070300006EA  2006       7          3          CA060307009      220060306G741410357479        SHAFT           BENDIX                  ROBSINR44   R44         7640120WP  LYC   O540  O540F1B5    41532EA                              MAGNETO         WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       790  663   L2294432E                                           DURING A 500 HR MAG INSPECTION, FOUND SHAFT FOR THE ROTATING MAGNET WORN BEYOND LIMITS.  BELIEVE SOMEONE HAD TRIED TO CHANGE THE COUPLING AND THEN COULD NOT PULL COUPLING OFF THE SHAFT.  THE NUT WAS REINSTALLED, TIGHTEN AND NEW COTTER PIN INSTALLED, BUT FAILED TO TORQUE THE NUT.  THIS IN TURN DID NOT LOAD THE SPACER PROPERLY WHICH THEN WORN THE SHAFT PREMATURELY.                                                                                                                                                                                                                                                                                                                                                                   1G71 3O3  O  H11NM   E295                 
20060626000672006062600067EA  2006       6          26         CA060307010      220060306G741410357426        DISTRIBUTOR BLK BENDIX                  ROBSINR44   R44         7640120WP  LYC   O540  O540F1B5    41532EA                              MAGNETO         WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            755   F189908E                                            (CAN) DURING A 500 HR INSPECTION FOUND DISTRIBUTOR BLOCK BUSHING WORN. THIS CAUSED THE GEAR TO WOBBLE.  WHEN THE GEAR WOBBLED THE ELECTRODE MADE CONTACT WITH THE BLOCK TERMINALS.  THIS CAUSED THE GEAR TO STRIP AND ELECTRODE TO BREAK. BUSHING POSSIBLY DID NOT HAVE ENOUGH LUBRICATION. (TC NR20060307010)                                                                                                                                                                                                                                                                                                                                                                                                                                  1G71 3O3  O  H11NM   E295                 
20060626000682006062600068NE  2006       6          26         CA060307011      220060306G741410357586        DISTRIBUTOR GEARBENDIX                  ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              MAGNETO         STRIPPED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            810   L26962SE                                            (CAN) REMOVED DUE TO ROUGH RUNNING ENGINE.  ONCE THE MAGNETO WAS INSPECTED FOUND DISTRIBUTOR GEAR TEETH WERE STIPPED. DUE TO POSSIBLE BACKFIRE ON ENGINE. (TC NR 20060307011)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1G71 3O3  O  H11NM   1E4                  
20060626000692006062600069    2006       6          26         CA060309001      420060208G22109960013         SWITCH                                  CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30015NE                              AUTOPILOT       FAILED          W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             CLCLIMB          1                      CA                                                                      (CAN) ON DEPARTURE, THE FLIGHT CREW REPORTED THEY HAD LOST THE AUTOPILOT, MACH TRIM AND THE STAB TRIM.  NR 1 STAB TRIM SWITCH WAS NOTICED TO BE STICKY AND HARD TO DISENGAGE. THE CREW WAS ADVISED THAT IT WAS PROBABLY THE NR 1 (CAPT'S) DISENGAGE SW (P/N 996-0013) AT FAULT AND CAUSING BOTH CHANNELS TO DISENGAGE AND THAT THE SWITCH NEEDED TO BE REPLACED. THE CREW CONTINUED ON IN A SLIGHTLY NOSE UP ATTITUDE AND THE AUTOPILOT UNSERVICEABLE. THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT AND THE SWITCH (P/N 996-0013) HAS BEEN REPLACED (TC NR 20060309001)                                                                                                                                                                         2L72 4F4  FRTA21EA   E15NE                
20060626000702006062600070EA  2006       6          26         CA060309002      220060225G7322                FUEL CONTROL                            CESSNA172   172M        2072418CE  LYC   O320  O320E2D     41508EA  MCAULY1C160 1C160DTM    GL                  UNSERVICEABLE   W      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN)  ON TAKEOFF, THE STATIC RPM WAS ABOUT 2200RPM. AFTER TAKE-OFF AT AN ESTIMATED 300-400FT AGL THE ENGINE FAIRLY ABRUPTLY DROPPED IN RPM AND THE AIRCRAFT BEGAN TO DESCEND. THE ENGINE WAS RUNNING ROUGH AND SOUNDED WEAK  BUT STILL RUNNING AT 2000 RPM.  PILOT THOUGHT (NOT SURE)HE PULLED ON CARB HEAT AND THEN TRIED TO WORK THE THROTTLE A BIT WITH NO SATISFACTORY RESPONSE. BY THE TIME THE AIRCRAFT WAS TAXIED TO THE HANGAR THE THROTTLE RESPONSE HAD RETURNED TO NORMAL.  (TC NR 20060309002)                                                                                                                                                                                                                                      1H71 3O3  ONT3A12    E274    5  NP910     
20060626000712006062600071NE  2006       6          26         CA060309003      220060219G7250                TURBINE BLADES                          BOEING727   727281      138408NNM  PWA   JT8   JT8D17      52049NE                              ENGINE          FAILED          W      ED  ENGINE SHUTDOWN         RETURN TO BLOCK                                                         EJ VIBRATION/BUFFET          WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA                                          709421                      (CAN) ON START UP THE CREW WAS UNABLE TO SUCCESSFULLY START THE NR 2 ENGINE.  LARGE PIECES OF TURBINE BLADES WERE DISCOVERED LAYING IN THE TAILPIPE AREA. THE ENGINE WAS REPLACED AND  A/C RETURNED TO SERVICE. (TC NR 20060309003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L73 4F4  F  A3WE    E2EA                 
20060626000722006062600072NM  2006       6          26         CA060309004      120060308G533065C32362        SKIN                                    BOEING737   737490      1384715NM                                                               BS 871-883      CHAFED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) FUSELAGE SKIN CHAFFING BS 871 TO 883 AT STR 1-2 L REPAIRED IAW EA 5330-02065 (TC NR 20060309004).                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F    RTA16WE                        
20060626000732006062600073CE  2006       6          26         CA060309005      120060307G55201016100197      RIVET           BEECH                   BEECH 200   200BEECH    1152920CE  PWA   PT6   PT642A           NE  HARTZLHCE4N HCE4N3      NE  TORQUE TUBE     LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3143                                                           (CAN) PHASE INSPECTION REVEALED SLIGHT MOVEMENT BETWEEN THE TORQUE TUBE AND THE ACTUATING ARM. THE ASSEMBLY IS SECURED BY 8 CHERRY LOCK RIVETS THAT WERE BEGINNING TO WORK, ALLOWING SUBTLE PLAY IN THE ASSEMBLED JOINT. TORQUE TUBE ASSEMBLY DETERMINED TO BE NON-REPAIRABLE AND WILL BE REPLACED. (TC NR 20060309005)                                                                                                                                                                                                                                                                                                                                                                                                                         1L72 4T4  T  A24CE   E4EA    5  CP10NE    
20060626000742006062600074CE  2006       6          26         CA060309007      120060308G733199103386        TRANSDUCER                              CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE  MCAULY3AF34C3GFR34C703  GL  CONNECTOR       FLUCTUATES      W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      CA       1037610376                                                     (CAN) DURING CRUISE FLIGHT FUEL FLOW INDICATOR STATED FLUCUATING FROM 80 LBS - 350 LBS/HR.  A/C RETURNED TO BASE AND UPON INSPECTION BY MAINT.  IT WAS DISCOVERED THAT THE CANNON PLUG ATTACHED TO THE FUEL FLOW TRANSDUCER WAS DIRTY.  CONNECTION WAS CLEANED, A/C GROUND RUN SERVICEABLE AND RETURNED TO SERVICE.  (MFG OF THE FUEL FLOW INDICATION IS: RIGAN DATA SYSTEMS) (TC NR 20060309007)                                                                                                                                                                                                                                                                                                                                               1H71 3T3  T  A37CE   E4EA    5  CP60GL    
20060626000752006062600075CE  2006       6          26         CA060310001      120060302G28104572            FUEL CAP                                LEAR  35    35LEAR      5170600CE  GARRTTTFE731TFE73122B   01518WP                              LT              LOOSE           W      JA  DUMP FUEL               UNSCHED LANDING                                                         KJ FLUID LOSS                WARNING INDICATION                                  CLCLIMB          1                      CA       8331                                                           (CAN) DURING TAKEOFF ROLL AND ATC NOTICED FUEL COMING OUT OF THE LT TIP TANK.  ATC CONTACTED THE CREW ABOUT THE SITUATION. THE CREW ELECTED TO DUMP FUEL FROM THE RT TIP TANK DUE TO FUEL IMBALANCE AND LAND THE AIRCRAFT WITH NO FURTHER INCIDENT.  THE FUEL CAP WAS FOUND BY AIRPORT MAINTENANCE CREW ON THE RUNWAY.  MAINTENANCE EXAMINED THE FUEL CAP AND NOTICED THE LOCKING MECHANISM HAD EXCESSIVE PLAY AND THE LOCKING TAB COULD EASILY BE TRIGGERED UNLOCK.  TECHNICIAN ALSO VERIFIED THE RT FUEL CAP AND NOTICED IT WAS ALSO DEFECTIVE.  BOTH CAPS WERE REPLACED. (TC NR 20060310001)                                                                                                                                                 2L72 4F4  F  A10CE   E6WE                 
20060626000902006062600090WP  2006       6          26         CA060310002      120060227G8011BC3151002       STARTER                                 ROBSINR44   R44         7640120WP  LYC   O540  O540F1B5    41532EA                              ENGINE          WEAK            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2887 1028                                                      (CAN) STARTER WOULD NOT TURN OVER ENGINE.  TROUBLESHOOTING REVEALED A STARTER PROBLEM.  STARTER WAS REPLACED, AND NO FURTHER DEFECTS WERE NOTED. (TC NR 20060310002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1G71 3O3  O  H11NM   E295                 
20060703000072006070300007    2006       7          3          CA060310005      420060308G2562MN1300          BATTERY         ACK                                                                                                                     ELT             CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                  043775                                              AT ANNUAL CERTIFICATION OF ELT, THE BATTERIES REMOVED FROM CASE FOR INSPECTION.  FOUND ONE BATTERY LEAKING CAUSING CORROSION ON THE BATTERY CONTACT AT BOTTOM OF CASE.  BATTERY CASE AND BATTERIES REPLACED ABD UNIT TESTED SATISFACTORY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 
20060703000082006070300008NE  2006       7          3          CA060310006      120060310G6321S6125203480     FLANGE                                  SKRSKYS61   S61A        814210CNE                                                               ROTOR BRAKE     FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      ATTEMPTED TO REPLACE A PART DAMAGED BEYOND REPAIR.  A PART WAS LOCATED AND ACQUIRED TO REPLACE DAMAGED UNIT.  PART WAS DELIVERED TO US FOR REVIEW.  SUPPLIER SUBMITTED VARIOUS CERTIFICATION DOCUMENTS TO VALIDATE PART.  PART JOURNAL IS UNDERSIZE AND IN NEED OF A CHROME REPAIR PER THE MANUAL.  THE ONLY DOCUMENT THAT WAS NOT SUPPLIED WAS AN 8130-03 ATTESTING THAT SIKORSKY HAD ACCEPTED THE MANUFACTURED PART AS AIRWORTHY.  ATTEMPTED TO CONTACT VENDOR ABOUT NEED OF THIS DOCUMENT, AND IT IS AT THIS TIME THAT IT WAS DISCOVERED THAT PART WAS AN OVERRUN PART.  TOLD VENDOR WE COULD NOT USE THE UNIT AND WOULD RETURN IT                                                                                                           2G72 4U      H2EA                         
20060705000322006070500032CE  2006       7          5          CA060310007      120060309G7830LJ78352005      ISOLATION VALVE                         LEAR  45    45LEAR      5170805CE  GARRTTTFE731TFE7312     01518WP                              THRUST REVERSER FAULTY          W      C   ABORTED TAKEOFF                                                                                 J  WARNING INDICATION                                                            TOTAKEOFF        1                      CA       55                                                             (CAN) ON TAKEOFF THE LT ENGINE INDICATION SHOWS AN AMBER (REV), WHICH MEANS THE LT THRUST REVERSER IS ARMED WHEN THE AIRCRAFT IS AIRBORNE AND/OR THE THRUST REVERSER IS ARMED WITH THE POWER LEVER ABOVE IDLE POSITION. THE CREW RETURNED. THE SYSTEM WAS TROUBLESHOT TO A DEFECTIVE PRESSURE SWITCH ON THE LT THRUST REVERSER ISOLATION VALVE.  AN ISOLATION VALVE ON ORDER. (TC NR 20060310007)                                                                                                                                                                                                                                                                                                                                               2L72 4F4  FRTT00008WIE6WE                 
20060705000332006070500033CE  2006       7          5          CA060310008      120060308G5270                SWITCH                                  LEAR  45    45LEAR      5170805CE  GARRTTTFE731TFE7312     01518WP                              PAX DOOR        MISRIGGED       W      B   EMER. DESCENT                                                                                   N  FALSE WARNING                                                                 CLCLIMB          1                      CA                                                                      (CAN) WHILE CLIMBING THRU FL400 THE CAS MESSAGE (ENTRY DOOR) ILLUMINATED, THERE WAS NO PRESSURIZATION PROBLEM AND NO WHISTLING SOUND. THE AIRCRAFT RETURNED WHERE AN AIRCRAFT MAINTENANCE ENGINEER INSPECTED THE DOOR AND CHECKED THE DOOR WARNING SWITCHES FOR PROPER RIGGING. DOOR SWITCHES WERE S-115, AND S-117 THRU S-121 WERE RE-RIGGED. SYSTEM WAS FUNCTION CHECKED AND THE AIRCRAFT RETURNED HOME. (TC# 20060310008)                                                                                                                                                                                                                                                                                                                    2L72 4F4  FRTT00008WIE6WE                 
20060705000422006070500042CE  2006       7          5          CA060313001      120060310G491070820262        SEAL                                    LEAR  45    45LEAR      5170805CE  GARRTTTFE731TFE7312     01518WP                              APU             MISSING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       956                                                            (CAN) AFTER EXPERIENCING DC POWER DIFFICULTIES OVER SEVERAL TIMES, FURTHER INSPECTION REVEALED WATER STAINS ON TOP OF THE LT AFT POWER DISTRIBUTION PANEL (PDP).  AFTER REMOVING THE PDP COVERS, WHITE POWDER ALUMINUM LIKE CORROSION WAS FOUND INSIDE THE COVERS.  INTERNAL PCB HAD 2 LARGE CORROSION SPOTS OVER SEVERAL CONTACTS.  FOUND DIRECTLY ON TOP OF THE LT AFT PDP WAS A MATING FLANGE FOR APU COOLING.  THIS FLANGE WAS LEAKING WATER FROM RAIN AND FREQUENT AIRCRAFT WASHING.  THE SEALING WAS FOUND TOO THIN ALL OVER THE FLANGE AND SEALING WAS COMPLETELY MISSING WHERE THE 4 RETAINING BOLTS WERE DUE TO FLIGHT VIBRATIONS OVER TIME. (TC NR 20060313001)                                                                       2L72 4F4  FRTT00008WIE6WE                 
20060705000442006070500044EA  2006       7          5          CA060313002      120060308G5514C6FSM182031     BUSHING                                 DHAV  DHC6  DHC6        2802606EA                                                               ADAPTOR         MISMANUFACTURED W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA                                                                      (CAN) THE RAISED BUSHING AREA OF THE ADAPTOR ARE NOT MACHINED AT THE CORRECT ANGLE. BOTH MACHINED SURFACES ARE ANGLED AFT, THIS CAUSES THE HORIZONTAL AND VERTICAL STABILZERS TO SIT OFF SET ON AN ANGLE AND NOT DOWN FLUSH.  MARKING ON THE ADAPTOR ALONG WITH THE PN ARE NR 451443, W/O 0928, AUG 11/99 AND FIRST ARTICAL. PLEASE REFER TO S/B 6/454 AND 6/516 FOR MORE DETAILS. (TC NR 20060313002)                                                                                                                                                                                                                                                                                                                                          1H72 3T    RTA9EA                         
20060705000452006070500045EU  2006       7          5          CA060313003      120060309G641010531980        BLADES                                  BOLKMS105   BO105S      5626006EU  ALLSN 250C  250C20B     03013GL                              TAIL ROTOR      INOPERATIVE     W      A   UNSCHED LANDING                                                                                 F  FLT CONT AFFECTED                                                             CRCRUISE         1                      CA                                                                      (CAN) AFTER FLIGHT, PILOT REPORTED THAT THE T/R PEDALS WERE STIFF.  PEDAL TENSION WAS CHECKED WITH THE AIRCRAFT RUNNING AND IN FLIGHT AND MEASURED AT 30 LBS TENSION. THE T/R BLADES WERE REPLACED BY SERVICEABLE UNITS AND PROBLEM DISAPPEARED, TENSION ON PEDALS RETURNED TO NORMAL AT 14 LBS. THE A/C WAS RETURNED TO SERVICE. (TC NR 20060313003)                                                                                                                                                                                                                                                                                                                                                                                           1G72 3U3  U  H3EU    E4CE                 
20060703000092006070300009SW  2006       7          3          CA060313004      120060308G29102781032776      LINE                                    SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE33111U   01514WP  MCAULY4HFR344HFR34C652  NE  HYD SYSTEM      CHAFED          W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      HYD FLUID LEAKING FROM LEFT ENGINE COMPARTMENT.  PRESSURE LINE FROM HYD PUMP TO FIREWALL FOUND CHAFED AND LEAKING.  LINE WAS CHAFED ON A UNION FITTING ON THE OIL TANK IN A "OUT OF VIEW" AREA.  LINE REPLACED, GEAR SWINGS CARRIED OUT, HYD RESEVOIR TOPPED UP AND AIRCRAFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4T4  TRTA8SW    E4WE    6  C3PNE     
20060703000172006070300017EU  2006       7          3          CA060313005      120060309G243523032027        STARTER GEN                             SNIAS 350   AS350BA     8680817EU  LYC   LTS101LTS101600A3 41560NE                              ENGINE          NOISY           W      E   ENGINE SHUTDOWN                                                                                 EH VIBRATION/BUFFET          ELECT. POWER LOSS-50 PC                             NRNOT REPORTED   1                      CA                                                                      VIBRATION ON START TO 60 PERCENT, AND STRANGE NOISE FROM THE ENGINE, FOUND BROKEN STARTER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3U3  UNCH9EU    E5NE                 
20060703000262006070300026WP  2006       7          3          CA060313006      120060310G6730D2121           SERVO                                   ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              MAIN ROTOR      LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA            132                                                       SERVO FOUND LEAKING FROM TOP AND BOTTOM OF CYLINDER BARREL.  SERVO REMOVED AND REPLACED WITH A SERVICEABLE UNIT.  THE ATTACHED PHOTOS SHOW THE SERVO AREAS THAT HAVE BEEN LEAKING.  THE BULK OF THE OIL HAS BEEN CLEANED OFF THE SERVO, BUT IT CAN STILL BE SEEN WHERE THE LEAKS WERE COMING FROM.                                                                                                                                                                                                                                                                                                                                                                                                                                              1G71 3O3  O  H11NM   1E4                  
20060703000272006070300027WP  2006       7          3          CA060313007      120060310G6730D2121           SERVO                                   ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              ROTOR           LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA            132                                                       SERVO WAS FOUND LEAKING FROM TOP AND BOTTOM OF CYLINDER BARREL.  SERVO WAS REMOVED AND REPLACED WITH A SERVICEABLE UNIT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1G71 3O3  O  H11NM   1E4                  
20060703000282006070300028NE  2006       7          3          CA060313008      120060307G29137665009808102   PUMP                                    SKRSKYS76   S76A        8143006NE  ALLSN 250C  250C30S     03013GL                              HYDRAULIC SYS   FAILED          W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      PUMP FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1G72 3U3  U  H1NE    E1GL                 
20060703000292006070300029NM  2006       7          3          CA060313009      120060312G4920170101106A      APU                                     BOEING737   737522      138449FNM  CFMINTCFM56 CFM563C1    13802EU                              APU BAY         FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA       28094                                                          AFTER A FLIGHT FROM A HOLIDAY RESORT, THE AIRCRAFT HAD LANDED AT HOME BASE AND WAS TAXIING TO THE GATE.  AN APU START WAS ATTEMPTED BUT THE UNIT WOULD NOT START.  ON INSPECTION, THE APU APPEARS TO HAVE HAD AN INTERNAL FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F4  FRTA16WE   E21EU                
20060703000302006070300030CE  2006       7          3          CA060313010      120060307G2435M230881320      BRUSHES         LUCAS                   CESSNA441   441         2076020CE                                                               STARTER GEN     BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       90   90    996                                                 SCHEDULED MX CHECK OF BRUSHES, OPERATOR FOUND 1 BRUSH HAMMERPLATE BROKEN OFF DURING INSPECTION OF BRUSHES.  RETURNED UNIT TO OVERHAUL AMO FOR REPAIRS.  UNIT HAS ONLY 90 HOURS TSO.  AMO FOUND ALL BRUSHES CHIPPED AT T/E AND WORN FROM OSCILLATION MOTION IN BRUSH HOLDERS.  ANOTHER BRUSH HAD A BROKEN HAMMERPLATE.  ARMATURE COMMUTATOR HAS ONE BAR PROTRUDING ABOVE TURNED DIA BY .003" IND RUNOUT.  MAX ALLOWED IS .0002".  ARMATURE HAD BEEN REWOUND AT OVERHAUL, SO HAS ONLY 90 HOURS ON IT.  STEEL HUB OF COMMUTATOR IS DARKENED, CONSISTENT WITH HIGH HEAT.  TO REPAIR, ARMATURE WAS REPLACED WITH REWOUND ONE, AND OEM REGULAR BRUSHES INSTALLED.  REMOVED ARMATURE AND BRUSHES ARE QUARANTINED.  WRITER IS CONCERNED THAT HIGHER INTE1L72 3T    RTA28CE                        
20060703000312006070300031SW  2006       7          3          CA060313011      120060202G6710212001181001    COLLECTIVE STICK                        BELL  212   212         1181420SW  PWA   PT6T  PT6T3       52045EA                              COCKPIT         BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3214                                                           THE AME WAS MANIPULATING THE COLLECTIVE STICK TO EXPOSE GREASE FITTINGS ON THE SWASHPLATE DURING A ROUTINE SERVICING OPERATION.  WHEN THE COLLECTIVE STICK WAS PULLED UP, STICK ASSY DETAIL P/N 212-001-181-001 BROKE AND SEPARATED AT THE SLOT WHERE THE NR 2 THROTTLE STOP PIN IS LOCATED, BETWEEN THE TWO THROTTLE GRIPS.                                                                                                                                                                                                                                                                                                                                                                                                                    1G71 4U4  U  H4SW    E22EA                
20060703000322006070300032EU  2006       7          3          CA060314001      120060309G5230A5247015100200  COVER                                   AIRBUS310   A310300     3930305EU  GE    CF6   CF680C2*         GL                              CARGO DOOR      MISSING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      THE AIRCRAFT ARRIVED FROM FLIGHT WITH ONE OF THE FORWARD CARGO DOOR ACCESS PANEL LATCH COVER MISSING.  DURING INVESTIGATION FOUND THE PANEL ATTACHMENT AREAS HAD ELONGATED, WHICH ALLOWED THE ATTACHMENT SCREWS TO PASS THROUGH THE ACCESS PANEL.  NEW PANEL ASSY WAS INSTALLED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F4  FRTA35EU   E23EA                
20060703000332006070300033    2006       7          3          CA060314002      420060202G2350GMA340          CIRCUIT BOARD   GARMIN INTL             DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO                              AUDIO PANEL     BURNED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1468       96266004                                            THREE GARMIN AUDIO PANELS GMA 340 HAD TO BE SENT BACK TO GARMIN FOR REPAIRS DUE TO A SHORT CIRCUIT OCCURRING WHEN PLUGGING IN HEADSETS WITH THE MASTER SWITCH ON.  FIRST WAS ON JANUARY 17, 2006, LAST TWO OCCURRED ON SAME DAY FEB 2, 2006.  OPERATING AIRCRAFT FOR A LITTLE MORE THAN TWO YEARS, SUSPECTED FIRST FAILURE MAY HAVE BEEN AN ISOLATED EVENT DUE TO FACT THAT REPLACEMENT OF UNIT, WITH A LOANER, FROM ATLANTIC AVIONICS, WORKED JUST FINE.  DIAMOND ISSUED SB DAC1-23-01 REV 0 TITLED DA20 C1 -  GMA 340 ISOLATION DIODES ISSUED 08 DECEMBER 2004.  NOT PROVIDED A COPY OF BULLETIN UNTIL AFTER FAILURES.                                                                                                                        1L71 3O3  ONTTA4CH   E7SO                 
20060703000342006070300034NM  2006       7          3          CA060314003      120060312G5100                UNKNOWN                                 BOEING737   737*               NM  PWA   JT8   JT8D17A     52049NE                                              MULTIPLE FAIL   W      A   UNSCHED LANDING                                                                                 SBHAFFECT SYSTEMS            SMOKE/FUMES/ODORS/SPARKS  ELECT. POWER LOSS-50 PC   CLCLIMB          1                      CA                                                                      WHILE CLIMBING THROUGH 15000 FT, THE FOLLOWING WAS ENCOUNTERED: CABIN EMERGENCY LIGHTS FLASHING. THRUST REVERSER ISOLATION VALVE OPEN ILLUMINATED.  NOSE GEAR UNSAFE INDICATION (GEAR RETRACTED).  DFDR ILLUMINATED.  CARGO OVERHEAT/DETECTION FAULT.  APU FAILED TO START WHEN SELECTED.  CAPTAIN HSI COMPUTER FLAG.  CSD LOW OIL PRESSURE ILLUMINATED.  ON SHORT FINAL, THE MAIN GEAR GREEN LIGHTS TURNED RED.  OVERHEAD MASTER CAUTION WOULD NOT EXTINGUISH.  AFTER TOUCH DOWN, THE FOLLOWING WAS FURTHER EXPERIENCED, NR 1 ENGINE THRUST REVERSER WOULD NOT OPERATE.  MAIN GEAR ILLUMINATED GREEN AND THEN BLACK.  VERY FAINT GEAR CONFIGURATION HORN SOUNDED FOR 30 SECONDS.  A FAINT ELECTRICAL SMELL WAS OBSERVED.  F/O STATED THAT IT WA2L72 4F4  FRTA16WE   E2EA                 
20060703000352006070300035CE  2006       7          3          CA060314004      120060313G329716001260        CIRCUIT BREAKER                         BEECH 90    F90         1152909CE  PWA   PT6   PT6A135     52043NE  HARTZLHCB4T HCB4TN3     GL  MLG             BROKEN          W      O   OTHER                                                                                           O  OTHER                                                                         APAPPROACH       1                      CA                                                                      LANDING GEAR FAILED TO EXTEND WHEN SELECTED.  POWERPACK C/B OPEN.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L72 4T4  T  A31CE   E4EA    6  CP40EA    
20060703000362006070300036EU  2006       7          3          CA060315001      120060314G6300332A67145620    BRACKET                                 SNIAS AS332 AS332L      8680809EU  TMECA MAKILAMAKILA1A    60040EU                              M/R DEICE SYSTEMCRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       186                                                            DURING A ROUTINE DAILY INSPECTION, TWO MAIN ROTOR DEICE BRACKET WERE FOUND TO HAVE CRACKS IN THE SAME AREA. THESE BRACKETS WERE REPLACED AND THE A/C RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2G72 4U4  U  H4EU    E12NE                
20060703000442006070300044NE  2006       7          3          CA060315002      220060314G72613037223         CARBON SEAL                             DHAV  DHC8  DHC8*              NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  NR 2 ENGINE     DAMAGED         W      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA            291                           120986                      IN CRUISE, AT FL200, OBSERVED SHORT INTERMITTENT ILLUMINATION OF OIL PRESS WARN LIGHT OF NR 2 ENG.  IND OF SLIGHT OIL PRESS FLUCTUATIONS OF CORRESPONDING GAUGE COUPLED WITH HIGHER OPERATING OIL TEMP ON NR 2 ENG.  CREW DECIDED TO DIVERT A/C TO BASE WHERE NORM APPROACH AND LANDING.  INVESTIGATION REVEALED SLIGHTLY LWR THAN NORM OIL LEVEL NR 2 ENG.  OIL LEVEL ADJUSTED TO MM LEVELS AND FOLLOWING SATIS ENG GROUND RUNS A/C RETURNED TO SERVICE.  FOLLOWING DAY OF OPERATION, INVESTIGATIONS WERE UNDERTAKEN TO ENSURE OIL CONSUMPTION NOT COMPROMISED AND DURING INVESTIGATIONS IT WAS REVEALED SEALING FACE OF BREATHER SYS CARBON SEAL DAMAGED WHICH COMPROMISED EFFICIENCY ON BREATHER SYSTEMS OP RESULTING IN INCREASED OIL CONSUM2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060705000772006070500077EU  2006       7          5          CA060315003      120060209G5610350A25902500    WINDSHIELD                              UROCOPEC130 EC130B4     8680989EU  TMECA ARRIELARRIEL2B         NE                              COCKPIT         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       926  926                                                       (CAN) DURING INSPECTION BEFORE FLIGHT THE PILOT FOUND A CRACK IN THE CENTER WINDSHIED. CRACK WAS IN THE LOWER RT CORNER AND WAS 4 INCHES LONG. CRACK WAS STOP DRILLED AND TAPED IAW ECC INSTRUCTION NR 8598.  CENTER WINDOW WAS REPLACED AT ECC. (TC NR 20060315003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1G72 3U3  U  H9EU    E00054EN             
20060703000452006070300045EA  2006       7          3          CA060315004      120060309G2434A700AP          RELAY                                   DHAV  DHC6  DHC6200     2802620EA  PWA   PT6   PT6A20      52043EA  HARTZLHCB3T HCB3TN3     GL  REVERSE CURRENT FAILED          W      O   OTHER                                                                                           H  ELECT. POWER LOSS-50 PC                                                       NRNOT REPORTED   1                      CA            603                                                       A/C SHUT DOWN AFTER FLT, CREW REPORTED NR 2 GENERATOR WARNING LIGHT DID NOT ILLUMINATE.  A/C WAS RUN FOR TROUBLESHOOTING, DURING WHICH TIME GEN FUNCTIONED INTERMITTENTLY.  WHEN ENGINES WERE SHUT DOWN, SMOKE BEGAN TO EMANATE FROM THE ELECTRICAL BAY IN THE CABIN CEILING.  ALL ELECT PWR WAS REMOVED FROM AIRCRAFT AND SMOKING STOPPED.  INVESTIGATION REVEALED THAT NR 2 REVERSE CURRENT RELAY HAD FAILED INTERNALLY AND WAS HEAVILY HEAT DAMAGED.  LARGE ELECTRICAL LEADS ATTACHED TO IT SHOWED SIGNS OF OVERHEATING AS WELL.  ALL DAMAGED WIRING WAS REPLACED, AS WELL AS THE RT REVERSE CURRENT RELAY AND THE RT VOLTAGE REGULATOR.  AIRCRAFT WAS RETURNED TO SERVICE.                                                                  1H72 3T3  TRTA9EA    E4EA    6  CP15EA    
20060703000462006070300046    2006       7          3          CA060315005      420060312G2330RDAV2133        MONITOR                                 BOEING757   757236      1384971NM  RROYCERB211 RB211535E43754555NE                              COCKPIT         ODOR            W      H   DEACTIVATE SYST/CIRCUITS                                                                        B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA            227                                                       ELECTRICAL BURNING SMELL FROM MONITOR.  MONITOR SWITCHED 'OFF'.  SMELL DISSIPATED.  MONITOR ELECTRICALLY DISCONNECTED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA2NM    E12EU                
20060703000472006070300047CE  2006       7          3          CA060315006      120060314G28231183890051      SHUTOFF VALVE                           BEECH 1900  1900C       1154161CE  PWA   PT6   PT6A65B     52043EA  HARTZLHCB4M HCB4MP3     GL  FUEL SYSTEM     UNKNOWN         W      K   NONE                                                                                            J  WARNING INDICATION                                                            ININSP/MAINT     1                      CA                                                                      DURING PRE FLIGHT INSPECTION, FUEL PRESSURE ANNUNCIATOR EXTINGUISHED WHILE THE FIRE WALL SHUTOFF VALVE T HANDLE WAS PULLED.  THIS INDICATED THAT THE VALVE WAS STILL OPEN.  DURING THE MX T/S IT WAS FOUND THAT VALVE POSITION INDICATOR ARM WAS CONTACTING THE FUEL FILTER BRACKET AND PREVENTING THE VALVE FROM CLOSING.  REWORK OF THE BRACKET GAVE ENOUGH CLEARANCE FOR THE VALVE TO OPERATE NORMALLY. THE RIGHT HAND SIDE WAS CHECKED AND THE VALVE WAS FROM A DIFFERENT MANUFACTURER AND HAD A MUCH SMALLER INDICATOR ARM. THIS WOULD NOT INTERFERE WITH THE BRACKET. THE MANUFACTURES PART NUMBERS ARE:  LEFT - ZMV13 (CIRCLE SEAL CONTROLS) RIGHT - AV24B1351BR.                                                                        2L72 4T4  TRTA24CE   E4EA    6  CP56GL    
20060703000482006070300048SW  2006       7          3          CA060315007      120060302G5347204072921009    YOKE                                    BELL  205   205A1       1181414SW  LYC   T53   T5313B      41549NE                              CARGO TRACK     CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      CRACKS ORIGINATING IN ATTACHMENT BOLT HOLES.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1G71 4U4  U  H1SW    E17EA                
20060703000952006070300095CE  2006       7          3          CA060316001      120060309G7160BAS2452502      CLAMP                                   RAYTHNDH125 HAWKER800XP 7150012CE  GARRTTTFE731TFE7315BR        WP                              RT INTAKE       FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2743                                                           DURING INSPECTION, RT ENGINE COWLING WAS OPENED AND TECHNICIAN FOUND PARTS OF RUBBER HOSE INSIDE COWLING.  FURTHER INVESTIGATION LEAD TO OPENING OF THE RT LOWER ACCESS PANEL WHERE THE CLAMP FOR THE RT LOW PRESSURE BLEED AIR TO THE MIXING VALVE DUCT WAS FOUND BROKEN AND PARTS OF THE RUBBER DUCT.  CLAMPS WERE FOUND NOT LOCKWIRED.  IT IS FELT THAT THE CLAMP FAILED LEADING TO THE FAILURE OF THE DUCT ASSEMBLY.  THE CREW HAD NO INDICATION OF DUCT FAILURE.  DUCT ASSEMBLY AND BOTH CLAMPS WERE REPLACED AND THE LT LOW PRESSURE DUCT TO MIXING VALVE WAS INSPECTED AND FOUND TO BE LOCKWIRED AND SECURED.                                                                                                                            2L72 4F4  FRTA3EU    E6WE                 
20060705000922006070500092CE  2006       7          5          CA060316002      120060227G2421                TERMINAL                                CESSNA182   R182        2072734CE  LYC   O540  O540J3C5    41532EA  MCAULY3D32C B3D32C407   GL  ALTERNATOR      BROKEN          W      K   NONE                                                                                            H  ELECT. POWER LOSS-50 PC                                                       TXTAXI/GRND HDL  1                      CA                                                                      PILOT REPORTED TOTAL LOSS OF ELECTRICAL POWER.  FOUND A BROKEN TERMINAL ON ALTERNATOR OUTPUT WIRE.  DURING THE GROUND RUN, FOLLOWING REPAIR, ENGINE STARTED NORMALLY FROM THE BATTERY WITHOUT CHARGING FIRST, AND CHARGING SYSTEM FUNCTIONED NORMALLY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3O3  ORT3A13    E295    5  CEXPP5C   
20060705000952006070500095GL  2006       7          5          CA060316003      220060314G73146896822         PUMP                                    BELL  206   206L3       1182108SW  ALLSN 250C  250C30P     03013GL                              ENGINE          LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA            2435                                                      AFTER COMPLETION OF 300 HR ENGINE INSPECTION ENGINE WAS BEING GND RUN AND LEAK CHECKED.  FUEL WAS NOTICED IN ENGINE COMPARTMENT AFTER INVESTIGATING DRAIN LINE WAS REMOVED FROM OVERBOARD DRAIN FOR FUEL PUMP AND EXCESSIVE LEAK WAS DETECTED.  PUMP REMOVED AND REPLACED WITH SERVICEABLE UNIT.                                                                                                                                                                                                                                                                                                                                                                                                                                                1G71 3U3  U  H2SW    E1GL                 
20060705000982006070500098CE  2006       7          5          CA060316004      120060306G572012212055        FITTING                                 CESSNA207   T207A       2073614CE  CONT  O520  TSIO520M    17040SO                              LT WING         GOUGED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       13764                                                          DURING WING REMOVAL FOR PAINT, LT LOWER WING STRUT FITTING WAS FOUND TO HAVE A GOUGE OF APPROXIMATELY 1/8" FROM STRUT FAIRING SCREW.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H71 3O3  O  A16CE   E8CE                 
20060705001042006070500104NM  2006       7          5          CA060316005      120060302G246050086003        CIRCUIT BREAKER                         BOEING727   727223      1384074NM  PWA   JT8   JT8D17      52049NE                              ELECTRICAL SYS  FAILED          W      A   UNSCHED LANDING                                                                                 GJ MULTIPLE FAILURE          WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      CREW REPORTED ON DEPARTURE/CLIMB-OUT, ALL FUEL TANK NR 1 AND NR 2 BOOST PUMP CB'S POPPED.  EXTENSIVE VISUAL INSPECTION OF PUMPS, WIRING CONNECTORS, ELECTRICAL HARNESSES AND SPLICES CARRIED OUT.  THE FOLLOWING COMPONENTS REPLACED: NR 2 GENERATOR HARNESS FROM FIRE WALL DISCONNECT TO GENERATOR REPLACED DUE TO HIGH RESISTANCE.  NR 1 GENERATOR CB (GCB) REPLACED DUE TO 47V DROP ACROSS T2-L2.  NR 2 GENERATOR CN (GCB) REPLACED, SUSPECT FAULT.  NR 1 GENERATOR CONTROL PANEL PRECAUTIONARY REPLACEMENT.  ALL CB'S RESET, SYSTEM FUNCTION TESTED SERVICEABLE.  NO FURTHER REPORTS.  THIS AIRCRAFT WAS IN STORAGE FOR PREVIOUS 18 MONTHS PRIOR TO RE-ENTERING SERVICE. THE DEFECTS APPEAR TO BE RELATED TO THIS STORAGE PERIOD.           2L73 4F4  F  A3WE    E2EA                 
20060705001052006070500105NM  2006       7          5          CA060316006      120060221G282291248075        RELAY                                   BOEING727   727223      1384074NM  PWA   JT8   JT8D17      52049NE                              FUEL SYSTEM     FAILED          W      A   UNSCHED LANDING                                                                                 GJ MULTIPLE FAILURE          WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      ALL 4 FUEL BOOST PUMP CIRCUIT BREAKERS POPPED IN FUEL TANK NR 2.  RECTIFICATION: 1 RELAY 109 ESS NR 2 BUS REPLACED.   MAINTENANCE DETERMINED L1 AND L2 TERMINALS SHORTED TOGETHER CAUSING INTERNAL DAMAGE.  LEFT AFT BOOST PUMP RELAY REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L73 4F4  F  A3WE    E2EA                 
20060705001062006070500106SW  2006       7          5          CA060316007      120060314G29107U7467          MANIFOLD                                BELL  206   206B        1181511SW  ALLSN 250C  250C20B     03013GL                              HYDRAULIC SYS   MALFUNCTIONED   W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             LDLANDING        1                      CA       12155                                                          DURING PILOT TRAINING AIRCRAFT COMPLETED A HYDRAULICS OFF LANDING.  HYDRAULIC SWITCH WAS THEN TURNED BACK ON AND THE FORE AND AFT MOVEMENTS CAME BACK HOWEVER THE LATERAL MOVEMENTS DID NOT COME BACK TO NORMAL HYDRAULIC ON.  AIRCRAFT WAS THEN SHUT DOWN AND HYDRAULIC SOLENOID/MANIFOLD WAS CHANGED.  SUSPECT OBSTRUCTION IN THE LATERAL SECTIONS OF THE MANIFOLD.  AIRCRAFT HAS SINCE RETURNED TO SERVICE AFTER ASSEMBLY WAS CHANGED.  DELAY IN REPORTING WSDR WAS DUE TO THE SYSTEM NOT GIVING ME FULL ACCESS TILL THE NEXT DAY.                                                                                                                                                                                                           1G71 3U3  U  H2SW    E4CE                 
20060705001072006070500107EA  2006       7          5          CA060316008      320060315G6111W69EK763        BLADE                                   DIAMONDA20  DA20C1      2990001GL                                   SNSNCHW69EK W69EK63     EA  PROPELLER       CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       20   20                                                        CRACK FOUND ON TRAILING EDGE OF PROPELLER TIP.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L71 3O    NTTA4CH           5  NTA4CH    
20060705001082006070500108SO  2006       7          5          CA060316009      220060301G8530                EXHAUST VALVE                           CESSNA150   150H        2071818CE  CONT  O200  O200A       17020SO  MCAULY1A101 1A101DCM    GL  ENGINE          STICKS          W      A   UNSCHED LANDING                                                                                 R  PARTIAL RPM/PWR LOSS                                                          CLCLIMB          1                      CA       1271 1271                                                      EXHAUST VALVE STICKY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1H71 3O3  O  3A19    E252    5  NP918     
20060705001092006070500109SO  2006       7          5          CA060316010      120060316G8011                GEAR                                    PIPER PA28  PA28140     7102802SO  LYC   O320  O320E3D     41508EA  SNSNCH74D   74DM        EA  STARTER BENDIX  CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA            1027                                                      THE STARTER BENDIX GEAR WAS BROKEN IN 3 THREE PLACES.  THE STARTER HOLD DOWN BOLTS WERE EITHER BROKEN OR STRETCHED.  SINCE THE STARTER AND ALT HAVE A SUPPORTING BRACE BETWEEN THEM, VERY STRONGLY SUSPECT THAT THE STARTER WAS ENGAGED WHILE THE ENGINE WAS RUNNING.  THE STARTER SW WAS CHECKED FOR DEFECTS BUT NONE FOUND.                                                                                                                                                                                                                                                                                                                                                                                                                   1L71 3O3  O  2A13    E274    5  NP88614   
20060705001102006070500110WP  2006       7          5          CA060316011      120060219G801172566           RING GEAR                               ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              STARTER         CHIPPED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       664                                                            TEETH FOUND MISSING DURING INSPECTION.  SERVICEABLE SUPPORT ASSEMBLY INSTALLED.  SUSPECT PROBLEM WITH THE STARTER/RING GEAR ENGAGEMENT.  A CHIPPED TOOTH WAS ALSO FOUND ON THE STARTER.  STARTER P/N BC315-100-4 WAS ALSO REPLACED AT THE SAME TIME.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1G71 3O3  O  H11NM   1E4                  
20060705000842006070500084CE  2006       7          5          CA060317001      120060314G323399810057652     ACTUATOR        BEECH                   BEECH 99    99          1154002CE  PWA   PT6   PT6A20      52043EA  HARTZLHCB3T HCB3TN3     GL  MLG             FAILED          W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                  890273                                              (CAN) ON DEPARTURE, A LOUD BANG WAS HEARD AFTER GEAR WAS SELECTED UP, LANDING GEAR (IN TRANSIT) LIGHT REMAINED ON. GEAR WAS CYCLED, NO FURTHER NOISES WERE HEARD, (IN TRANSIT) LIGHT REMAINED ON. PASSENGER SEATED IN REAR ADVISED PILOT, RT MLG WAS NOT RETRACTING. PILOT SELECTED GEARDOWN AND OBSERVED THAT ALL 3 GREEN, GEAR DOWN AND LOCKED LIGHTS WERE ILLUMINATED. AC WAS FLOWN WITH GEAR DOWN AND LANDED WITHOUT INCIDENT. AC WAS JACKED UP, A GEAR SWING CARRIED OUT, NOTED THAT DRIVE TO RT MLG ACTUATOR WAS ROTATING, ACTUATOR WOULD NOT EXTEND OR RETRACT, REPLACED, AC RETURNED TO SERVICE. WHEN ACTUATOR WAS TESTED DRIVE WAS ROTATED AND THERE WAS SLIGHT RESISTANCE FELT, PINION DID NOT ENGAGE SCREW HSG.                      1L72 3T3  T  A14CE   E4EA    6  CP15EA    
20060913002882006091300288CE  2006       9          13         CA060317002      120060310G33972B1PECC532000   CONNECTOR                               LEAR  35    36A         5170603CE  GARRTTTFE731TFE7312     01518WP                              GLARESHIELD     SHORTED         W      A   UNSCHED LANDING                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA       15303                                                          (CAN) AIRCRAFT DEPARTED APPROXIMATELY 30 MINUTES AFTER DEPARTURE SMOKE WAS NOTED UNDER GLARESHIELD AND EMERGENCY LANDING EXECUTED. MAINTENANCE PERSONNEL FOUND SOURCE OF SMOKE TO BE GLARESHIELD FLOODLIGHT. MAINTENANCE DE-ACTIVATED FLOODLIGHTING BY PULLING/COLLARING CIRCUIT BREAKER AND DEFERRING FLOODLIGHT IAW MEL. AIRCRAFT RETURNED TO HOME. FURTHER TROUBLESHOOTING REVEALED COAX CONNECTOR/COAX WAS SHORTED WHERE IT ATTACHES TO GLARESHIELD FLORESCENT LAMP ASSEMBLY.  (TC NR 20060317002)                                                                                                                                                                                                                                          2L72 4F4  F  A10CE   E6WE                 
20060705000932006070500093    2006       7          5          CA060317003      120060317G3210CRS8517319      BUSHING                                                                                                                                 MLG             CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) 16 NEW BUSHINGS RECEIVED, P/N CRS85-173-19 ALL FAILED NDT REQUIREMENT PRIOR TO INSTALL DUE TO CRACK IN THE BORE AREA.   (TC NR 20060317003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         
20060705000942006070500094GL  2006       7          5          CA060317004      120060316G3246C2UT473         TORQUE TUBE                             DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE  HARTZLHCB3R HCB3R304    GL  WATER RUDDER    FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) WHILE TAXING FLOAT EQUIPED AIRCRAFT, PILOT HAD COMPLETE FAILURE OF WATER RUDDER STEERING SYSTEM.  UPON INSPECTION IT WAS FOUND THAT THE TORQUE TUBE HAD CRACKED, SPLITTING INTO TWO PIECES.  FURTHER VISUAL INSPECTION FOUND THAT THE TORQUE TUBE WAS SEVERLY CORRODED INSIDE.  THIS CORROSION WAS MOST LIKELY CAUSED FROM WATER COLLECTING INSIDE THE TUBE DUE TO LACK OF DRAINAGE BECAUSE OF THE TILLER BAR WHICH IS ATTACHED HORIZONTALLY AT THE BASE OF THE VERTICAL TORQUE TUBE. (TC NR 20060317004)                                                                                                                                                                                                                                 1H71 3R3  RRCA806    5E1     5  CP28EA    
20060626000222006062600022SW  2006       6          26         CA060317007      120060213G5520214001920101    HORN            BELL                    BELL  214   214B1       1182105SW                                                               ELEVATOR        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1468       RE225                                               CRACK FOUND ON ELEVATOR HORN ASSY ON REGULAR INSPECTION.  REMOVED FROM SERVICE AND REPLACED WITH NEW ASSEMBLY.  PART HAS A RETIREMENT LIFE OF 2500 HOURS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2G71 4U      H6SW                         
20060626000232006062600023EA  2006       6          26         CA060317008      220060315G73143034794         PUMP                                    BEECH 90    C90A        1152911CE  PWA   PT6   PT6A21      52043EA  HARTZLHCB3T HCB3TN3     GL  FUEL SYS        LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA            1037                                                      VISUAL INSPECTION CARRIED OUT IAW SERVICEABILITY CHECK. PRE-DISPATCH CHECK NOTICED FUEL UNDER THE RT ENGINE.  INSPECT FUEL FILTER AND DRAINS WITH THE BOOST PUMP ON AND NO LEAKAGE WAS FOUND.  REMOVED FUEL PUMP DRAIN HOSE AND A LARGE AMOUNT OF FUEL WAS EXPELLED FROM THE FUEL PUMP DRAIN.  THE FUEL PUMP/FUEL CONTROL ASSEMBLY WAS REMOVED FROM SERVICE DUE TO SUSPECTED INTERNAL BEARING WASHOUT DUE TO SEAL FAILURE.                                                                                                                                                                                                                                                                                                                      1L72 3T4  TRT3A20    E4EA    6  CP15EA    
20060626000242006062600024CE  2006       6          26         CA060317009      120060317G2435                BEARING         LEARSIEGLER             BEECH 90    C90A        1152911CE  PWA   PT6   PT6A21      52043EA  HARTZLHCB3T HCB3TN3     GL  STARTER GEN     FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            493   16110                                               VISUAL INSPECTION CARRIED OUT IAW OPERATION FOUR.  NOTICED METAL DUST ON BACK OF THE ACCESSORY GEARBOX AND FOUND IT TO BE MAGNETIC.  REMOVED STARTER GENERATOR AND FOUND THE QUILL SHAFT BEARING HAD FAILED.  UNIT WAS REMOVED FROM SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L72 3T4  TRT3A20    E4EA    6  CP15EA    
20060626000252006062600025CE  2006       6          26         CA060317010      120060311G323350820285        ACTUATOR        BEECH                   BEECH 200   B200        1152922CE  PWA   PT6   PT6A64           EA                              NLG             SEIZED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            CLCLIMB          1                      CA            1912                                                      NOSE LANDING GEAR ACTUATOR SEIZED AND OVER-LOADED MLG MOTOR BREAKER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L72 4T4  T  A24CE   E4EA                 
20060626000342006062600034CE  2006       6          26         CA060317011      120060314G2910                HYDRAULIC SYSTEM                        BEECH 200   200CBEECH   1152926CE  PWA   PT6   PT6A41      52043EA  HARTZLHCD4N3HCD4N3A     GL                  LEAKING         W      K   NONE                                                                                            KS FLUID LOSS                AFFECT SYSTEMS                                      ININSP/MAINT     1                      CA       14914                                                          ON INVESTIGATING A HYDRAULIC LEAK IN THE NR 1 GEAR WELL AREA, CRACKS WERE NOTED IN THE CHANNELS P/N 101-120025-57 AND P/N 101-120025-55 AS WELL AS THE ANGLE'S P/N 101-120025-67 AND 101-120025-68.  THE A/C HAD A HYDRAULIC GEAR INSTALLED IN 1988 (REPLACING THE MECHANICAL GEAR ACTUATORS), AND AT THAT TIME HAD 2403.9 HOURS ON THE AIRFRAME.  THE NR 2 GEAR WELL WAS INSPECTED FOR SIMILAR DAMAGE AND NONE WAS NOTED.  THE AFFECTED PARTS WERE REPLACED GEAR SWINGS ACCOMPLISHED AND THE A/C RETURNED TO SERVICE.                                                                                                                                                                                                                          1L72 4T4  T  A24CE   E4EA    5  CSTC      
20060705000972006070500097EU  2006       7          5          CA060317012      120060311G2797                WIRE                                    PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  TE FLAPS        FAILED          W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             LDLANDING        1                      CA       11782                                                          (CAN) FLAPS FAILED TO EXTEND ON LANDING. FLAPS WORKED INTERMITTENTLY IN THE HANGER. VARIOUS FAULTS CODES WERE NOTED BUT THEY WERE NOT CONSISTENT AFTER RESETTING THE SYSTEM. UPON FURTHER INVESTIGATION IT WAS NOTED THAT THE WIRES TO THE P029 PLUG TO THE FCWU HAD FAILED INSULATION ABOUT A INCH BACK FROM THE PLUG UNDERNEATH THE FIRST CLAMP.  DAMAGED SECTION OF THE WIRING WAS REMOVED AND THE PLUG REPLACED. FLAPS WERE RESET ETC. AND OP'S CHECKED NORMAL. THIS PLUG AND WIRING WERE INSTALLED AS PART OF SB 27008 WHICH WAS INCORPORATED ON THE A/C AT 26 AFTT AND 12 TC. (TC NR 20060317012)                                                                                                                                         1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20060705000992006070500099EA  2006       7          5          CA060318001      120060315G4950WE38007703      APU                                     CNDAIRCL600 CL6002C10   1390015EA                                                                               ODOR            W      C   ABORTED TAKEOFF                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      TOTAKEOFF        1                      CA       3891                                                           (CAN) CREW REPORTED SMOKE AFT LAV WARNING MSG ABORTED T/O AND EVACUATED PAX THROUGH MAIN DOOR ON RUNWAY. REPORTED SMELL ONLY, NO VISIBLE SMOKE. SOURCE OF SMOKE SMELL BELIEVED TO BE APU BLEEDS. APU WAS REPLACED IAW AMM. (TC NR 20060318001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F    RTA21EA                        
20060705001002006070500100EA  2006       7          5          CA060318002      120060312G3234601R7520617     SELECTOR VALVE                          CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              NLG             FAILED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            APAPPROACH       1                      CA       2507                                                           (CAN) A GEAR DISAGREE MESSAGE ON EICAS ALONG WITH MASTER WARNING AFTER GEAR DOWN SELECTION.  ON INVESTIGATION, IT WAS NOTED NLG DID NOT SHOW DOWN AND LOCKED.  DOING A FLY BY, CONTROL TOWER WAS ABLE TO VERIFY THE NLG WAS NOT DOWN.   CREW PROCEEDED WITH QRH PROCEDURES AND ACTIVATED MANUAL RELEASE HANDLE WITHOUT OBTAINING THE DESIRED RESULT.  THE MLG HANDLE WAS THEN CYCLED AND ONLY THEN DID THE GEAR INDICATE DOWN AND LOCKED.  AN EMERGENCY WAS DECLARED. THE AIRCRAFT LANDED WITHOUT FURTHER EVENT. MAINTENANCE REPLACED THE NLG SELECTOR VALVE AND UPLOCK ACTUATOR.  ALL SUBSEQUENT CHECKS IAW AMM.  AIRCRAFT WAS RELEASED BACK TO SERVICE.  NLG UPLOCK ACTUATOR P/N 1660-103, S/N NGL10329/99 TSN 15283.42 (TC NR20060318002)    2L72 4F4  FRTA21EA   E15NE                
20060705001012006070500101EA  2006       7          5          CA060319001      120060319G5610                WINDSHIELD                              CNDAIRCL600 CL6002B19   1900309EA                                                               COCKPIT         FAILED          W      A   UNSCHED LANDING                                                                                 BA SMOKE/FUMES/ODORS/SPARKS  FLAME/FIRE                                          CLCLIMB          1                      CA                                                                      (CAN) APROX 19 MIN AFTER TAKEOFF, AIRCRAFT REPORTED SMOKE, SPARKS AND FIRE IN THE COCKPIT, COMING FROM THE PILOTS WINDSHIELD. WINDSHIELD HEAT WAS IMMEDIATELY SWITCHED OFF AND FIRE/SPARKS EXTINGUISHED.  AIRCRAFT RETURNED TO BLOCKS.  INITIAL VERBAL REPORT FROM MAINTENANCE CONTROL INDICATES THAT THE PILOT WINDSHIELD HEAT TERMINAL BLOCK IS BURNED, THERE IS SOME SOOT ON THE COCKPIT CELING PANEL AND A SMALL PORTION(TC NR  20060319001)                                                                                                                                                                                                                                                                                                2L72 4F    RTA21EA                        
20060627000022006062700002GL  2006       6          27         CA060320001      320060316G6110311466001       SEAL                                    BEECH 90    C90A        1152911CE  PWA   PT6   PT6A21      52043EA  HARTZLHCB3T HCB3TN3     GL  PROPELLER       DAMAGED         W      E   ENGINE SHUTDOWN                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA       1                                  PCE25397                    IN CRUISE 16,000 FT, NOTICED OIL LEAK ON TOP RT FWD ENG COWL. LEAK PROGRESSIVELY GOT WORSE, PILOTS ELECTED TO RETURN TO BASE. EVEN THOUGH ENG OIL TEMP AND PRESS NORM, PILOTS SHUTDOWN RT ENG.  CREW DECLARED EMERG.  BECAUSE QTY OF OIL LOST, PROP SHAFT SEAL SHOULD BE LOOKED AT.  RT PROP SEAL HAD BEEN REPLACED 2 DAYS EARLIER DUE TO OIL LEAKAGE IN NOSE CASE AREA. MX FOUND FAULTY PROP SEAL WAS WRONG P/N.  BY TIME OF DISCOVERY OUR P & W FSR WAS ON SITE, WENT BACK TO OUR STORES AND PULLED THE REMAINING SEAL IN STOCK STAMPED 3114661-01, AND IT TO WAS WRONG PART INSIDE, (3114660-01).  WITNESSED BY FSR.  SEALS CAME FROM CPWA, PACKAGED ON 02/2000.  BECAUSE OF LOSS OF OIL/AIR PRESSURE IN THE RGB, OIL WAS ALLOWED TO MIGRATE 1L72 3T4  TRT3A20    E4EA    6  CP15EA    
20060913002892006091300289CE  2006       9          13         CA060320002      120060315G27506627503000019   TRANSDUCER                              LEAR  45    45LEAR      5170805CE  GARRTTTFE731TFE7312     01518WP                              TE FLAP CONTROL MALFUNCTIONED   W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA       68                                                             (CAN) ON THE FLIGHT WITH A SCHEDULED REFUELING STOP. WHILE IN CRUISE APPROXIMATIVELY 1.5 HOURS AFTER DEPARTURE, THE AMBER CAS MESSAGE (FLAP FAIL) ILLUMINATED. THE CREW WAS UNABLE TO RESET THE SYSTEM AND MADE A FLAP LESS LANDING, INSTEAD OF WHERE AUTHORIZED SERVICE FACILITY WAS ABLE TO CONNECT THE DIAGNOSTIC COMPUTER TO THE AIRCRAFT. THE FAULT HAD ALREADY RESET ITSELF AND THE GROUND CREW WAS UNABLE TO DUPLICATE THE PROBLEM. THE AIRCRAFT WAS RETURNED TO SERVICE. ON THE FLIGHT THE AMBER CAS MESSAGE (FLAP FAIL) ILLUMINATED AND THE AIRCRAFT MADE A FLAPLESS LANDING. A TEAM OF TECHNICIANS FROM SERVICE CENTER WAS DISPATCHED TO THE AIRCRAFT WHERE TROUBLESHOOTING WAS PERFORMED. THE TECHNICIANS WERE UNABLE TO DUPLICATE TH2L72 4F4  FRTT00008WIE6WE                 
20060623000172006062300017CE  2006       6          23         CA060320003      120060309G55201156100153      SUPPORT BRACKET BEECH                   BEECH 100   A100        1152915CE  PWA   PT6   PT6A28           EA  HARTZLHCD4N3HCD4N3A     GL                  CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN)  CRACK FOUND ON IB SUPPORT BRACKET WHILE CARRYING OUT REPETITVE INSPECTION MSB 2145.  TORQUE TUBE REPLACED WITH NEW.  (TC NR 20060320003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L72 3T4  T  A14CE   E4EA    5  CSTC      
20060623000182006062300018WP  2006       6          23         CA060320004      120060320G1100369A81433       DATA PLATE                              HUGHES369   369D        4470706WP  ALLSN 250C  250C20B     03013GL                              FUEL TANK       LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) GLUE ON DATA TAG DETERIORATED DUE TO CONTACT WITH FUEL AND WAS LOCATED AT BOTTOM OF FUEL TANK (TC NR 20060320004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1G71 3U3  U  H3WE    E4CE                 
20060705001022006070500102NM  2006       7          5          CA060320005      120060320G3231CL12068161      SOCKET                                  BOMBDRDHC8  DHC8402     1390042NM                                                               MLG DOOR        BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING C-CHECK, FUNCTIONAL CHECK ON TASK CARD 3230/15 (OPERATIONAL CHECK OF LANDING GEAR DOOR SEQUENCE CONTROL CIRCUIT) DOES NOT WORK. AFTER INVESTIGATION, RELAY (3260-K9) SOCKET FOUND BROKEN AND PINS OLDER SOCKET UNGLUED. WIRE WERE FOUND HANGING LOOSE WITH A HI RISK OF CONTACT WITH STRUCTURE. POSSIBILITY OF (WOW) CIRCUIT FAILURE AND THE MOST IMPORTANT, IMPOSSIBILITY OF GEARS EXTENSION IN ALTERNATED RELEASE IN CASE OF EMERGENCY EXTENSION. (TC NR 20060320005)                                                                                                                                                                                                                                                            2H72 4T    RTA13NM                        
20060705001032006070500103    2006       7          5          CA060320006      220060310G732121195761011     ECU                                     BOMBDRBD700 BD7001A10   1390006GL                                                               ENGINE          INOPERATIVE     W      O   OTHER                                                                                           RY PARTIAL RPM/PWR LOSS      ENGINE STOPPAGE                                     CLCLIMB          1                      CA                                                                      (CAN) THE PROBLEM OCCURED ON THE 11/03/2006. DUE TO INTERNET CAPACITY TO DISPLAY THE RIGHT DATE, THE DATE OF MARCH 10 WAS WRITTEN IN THE (OCCURENCE DATE) ABOVE DUE TO INTERNET INCAPACITY TO DISPLAY CERTAIN DATE.  FLIGHT CREW NOTICED A LT ENGINE ROLL BACK AT CLIMB. PROBLEM OCCURED TWICE BEFORE ENGINE FLAMED OUT. ENGINE AUTO RESTARTED. WAS FINE FOR THE REST OF THE FLIGHT.  AMBER FADEC FAIL CAS POSTED.  AFTER LANDING LT T/R WOULD NOT STOW.  3-13-06 REPLACED LT ENGINE FADEC ECU A AND RT ENGINE FADEC ECU B REMOVED AS A PRECAUTIONARY MEASURE. GROUND RUNS OPS CHECKS GOOD.                                                                                                                                                     2L72 4F    RTT00003NY                     
20060705001222006070500122EA  2006       7          5          CA060320008      120060315G5610NP1393225       WINDOW                                  CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              COCKPIT         CRACKED         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) EN ROUTE DISCOVERED 2 CRACKS IN LT SIDE WINDOW, DIVERTED.  LT SIDE WINDOW REPLACED AND TESTED IAW AMM PROCEDURE.  AIRCRAFT RETURNED TO SERVICE. (TC NR 20060320008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F4  FRTA21EA   E15NE                
20060711001202006071100120EU  2006       7          11         CA060321001      220060316G7310                FUEL FILTER                             BRAERO748   HS7482A     4231001EU  RROYCEDART  DART5342         EU  ROTOL R4304 R2124304    EU  ENGINE          FAILED          W      C   ABORTED TAKEOFF                                                                                 J  WARNING INDICATION                                                            TOTAKEOFF        1                      CA                                                                      (CAN) DEPARTING, THE CREW OBSERVED A FUEL FILTER INDICATION ON NR 2 ENGINE. THE TAKEOFF WAS REJECTED AND THE AIRCRAFT RETURNED TO THE COMPANY RAMP. MAINTENANCE REPLACED THE FILTER AND AFTER SATISFACTORY GROUND RUN THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060321001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 3T4  T  A24EU   A196    6  CP899     
20060705002002006070500200NM  2006       7          5          CA060321002      120060317G3240214747          BRAKE                                   BOEING737   737522      138449FNM  CFMINTCFM56 CFM563C     13802EU                                              FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         LDLANDING        1                      CA                                                                      (CAN) UPON LANDING ( MONCTON ) WITH THE ANTI-SKID SYSTEM OPERATING UNDER MEL 32-2 (ANTI-SKID SYSTEM INOP), THE AC LANDED ON A BARE RUNWAY AND BLEW 3 MAIN WHEEL TIRES AND BADLY SCUFFED THE FOURTH.  ALL FOUR MAIN TIRES REPLACED. AIRCRAFT FERRIED. UPON FURTHER INVESTIGATION,THE NOSE GEAR SAFETY SENSOR AND E11 CIRCUIT CARD WERE REPLACED.  FURTHER INVESTIGATION ON-GOING. TIMES: 37418:14   CYCLES: 22960  (TC NR 20060321002)                                                                                                                                                                                                                                                                                                           2L72 4F4  FRTA16WE   E21EU                
20060705002012006070500201NM  2006       7          5          CA060321003      120060321G52436556235159      DOOR                                    BOEING727   727247      138408FNM                                                               HYD BAY         MISSING         W      O   OTHER                                                                                           D  INFLIGHT SEPARATION                                                           CLCLIMB          1                      CA       68406                                                          (CAN) AIRCRAFT WAS LEAVING ON-ROUTE. SHORTLY AFTER TAKEOFF AT APPROX. 12000 FT. THE CREW NOTICED A VIBRATION. ALL INDICATIONS WERE NORMAL AND THE AIRCRAFT CONTINUED. AFTER TAXIING TO THE RAMP THE MAINTENANCE PERSON NOTICED THAT THE HYDRAULIC SERVICING BAY DOOR WAS MISSING. AN INVESTIGATION WAS PERFORMED AND IT WAS FOUND THAT THE MAINTENANCE PERSON HAD NOT CLOSED THE DOOR PROPERLY. NOT ALL LATCHES HAD NOT BEEN CLOSED PROPERLY. SERVICEABLE DOOR AND HINGE WAS INSTALLED AND THE AIRCRAFT WAS INSPECTED. THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060321003)                                                                                                                                                                2L73 4F      A3WE                         
20060705002022006070500202WP  2006       7          5          CA060321004      220060317G7397C8102414        CABLE                                   SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP  HARTZLHCE4N HCE4N3      NE                  BROKEN          W      E   ENGINE SHUTDOWN                                                                                 O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) FLIGHT CREW REPORTED THAT DURING START THE RPM WAS UNCONTROLLABLE AND INITIATED A MANUAL SHUT DOWN. MAINTENANCE DISCOVERED THE POWER LEVER BROKEN APPROX. 4 INCHES FROM THE END JUST SHORT OF THE QUICK DISCONNECT FITTING.  DUE TO THE FACT THAT THE TELE-FLEX CABLE IS LOCATED INSIDE A (SHEATH) THE DEFECT IS NOT DETECTABLE UNTIL THE CABLE BREAKS. IT APPEARS AS THOUGH THE CABLE HAS BEEN CONTACTING THE INNER PORTION OF THE SHEATH FOR SOME TIME AND THE FACT THAT THE PILOTS PULL THE POWER LEVER INTO REVERSE EVERY SHUT DOWN CAUSED SOME WORK HARDENING OF THE MATERIAL WHICH ULTIMATELY CAUSED IT TO FAIL. (TC NR 20060321004)                                                                                                2L72 4T4  TRTA8SW    E4WE    5  CP10NE    
20060705002032006070500203EA  2006       7          5          CA060321005      120060321G2810CL21564001      FUEL CELL                               CNDAIRCL215 CL2156B11215       EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF15      NE  LT WING         LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       1220                                                           (CAN) WHILE UNDERGOING A SCHEDULED INSPECTION FUEL WAS FOUND DRIPPING FROM THE LT WING. ALL 8 FUEL TANKS WERE REMOVED FOR LEAK CHECK. THIS AND SEVERAL OTHER CELLS WERE FOUND LEAKING INCLUDING THIS ONE. DEFECTIVE CELLS WILL BE REPLACED. (TC NR 20060321005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2H72 4T4  TRTA14EA   E20NE   6  CP7NE     
20060705001182006070500118EA  2006       7          5          CA060321006      120060321G2820CL215640026     FUEL CELL                               CNDAIRCL215 CL2156B11215       EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  NR 2            LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       1222                                                           WHILE UNDERGOING A SCHEDULED INSPECTION FUEL WAS FOUND DRIPPING FROM THE LEFT WING.  ALL 8 FUEL TANKS WERE REMOVED FOR LEAK CHECK.  THIS AND SEVERAL OTHER CELLS WERE FOUND LEAKING INCLUDING THIS ONE.  DEFECTIVE CELLS WILL BE REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2H72 4T4  TRTA14EA   E20NE   6  CP7NE     
20060705001192006070500119EA  2006       7          5          CA060321007      120060321G2820CL215640022     FUEL CELL                               CNDAIRCL215 CL2156B11215       EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  NR 6            LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       1222                                                           DURING A SCHEDULED INSPECTION IT WAS OBSERVED THAT THE LEFT WING WAS LEAKING FUEL.  ALL 8 FUEL CELLS WERE REMOVED FOR LEAK CHECK AND 6 OUT OF 8 WERE FOUND LEAKING INCLUDING THIS ONE.  LEAKING CELLS WILL BE REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2H72 4T4  TRTA14EA   E20NE   6  CP7NE     
20060705002042006070500204EA  2006       7          5          CA060321008      120060321G2810CL21564002      FUEL CELL                               CNDAIRCL215 CL2156B11215       EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF15      NE  LT WING         LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       1222                                                           (CAN) DURING A SCHEDULED INSPECTION IT WAS OBSERVED THAT THE LT WING WAS LEAKING FUEL.  ALL 8 FUEL CELLS WERE REMOVED FO LEAK CHECK AND 6 OUT OF 8 WERE FOUND LEAKING INCLUDING THIS ONE. LEAKING CELLS WILL BE REPLACED. (TC NR 20060321008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2H72 4T4  TRTA14EA   E20NE   6  CP7NE     
20060705002082006070500208EA  2006       7          5          CA060321009      120060321G2810CL21564075      FUEL CELL                               CNDAIRCL215 CL2151A10   1900320EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF15      NE  LT WING         LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       1222                                                           (CAN) DURING A SCHEDULED INSPECTION IT WAS OBSERVED THAT THE LEFT HAND WING WAS LEAKING FUEL. ALL 8 FUEL CELLS WERE REMOVED FOR LEAK CHECK AND 6 OUT OF 8 WERE FOUND LEAKING INCLUDING THIS ONE. LEAKING CELLS WILL BE REPLACED. (TC NR 20060321009)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2H72 4R4  TRTA14EA   E20NE   6  CP7NE     
20060705002202006070500220GL  2006       7          5          CA060321011      120060130G5344C2FS3282A       STRUT                                   DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE  HARTZLHCB3R HCB3R304    GL  DOOR POST       FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       29083                                                          (CAN) ULTRASONIC INSPECTION REVEALED THAT THE RT DOOR POST STRUT HAD FAILED THE INSPECTION CRITERIA.  NEW DOOR POST STRUTS INSTALLED. (TC NR 20060321011)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3R3  RRCA806    5E1     5  CP28EA    
20060705001372006070500137GL  2006       7          5          CA060321012      120060303G5311C2FS3203A       TUBE                                    DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE  HAMSTD2D    2D30        NE  BIRD CAGE       UNSERVICEABLE   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            4497                                                      DIAGONAL BIRD CAGE TUBE FOUND TO BE BELOW LIMITS DURING ULTRASONIC INSPECTION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H71 3R3  RRCA806    5E1     5  CP206     
20060705001382006070500138EA  2006       7          5          CA060321013      120060203G5342C3FS4727        HINGE BRACKET                           DHAV  DHC3  DHC3        2800202EA  PWA   R1340 R134059     52016NE                              HORIZ STAB      DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       23509                                                          BOTH THE FORWARD HORIZONTAL STABILIZER ATTACH HINGE BRACKETS (C3FS472-7 RT AND C3FS473-7 LT) WERE FOUND TO BE BUSHED BEYOND SERVICEABLE LIMITS.  VIKING AIR HAD GIVEN A MAXIMUM OD OVERSIZE BUSHING OF .500.  DURING INSPECTION THE BUSHINGS WERE MEASURED AT .650 + BOTH BRACKETS WERE REPLACED WITH NEW PARTS.                                                                                                                                                                                                                                                                                                                                                                                                                                1H71 3R3  R  A815    5E2                  
20060705001462006070500146EA  2006       7          5          CA060321014      120060201G5700C3FS145         BAR                                     DHAV  DHC3  DHC3        2800202EA  PWA   R1340 R134059     52016NE                              WING            CORRODED        W      O   OTHER                                                                                           O  OTHER                                                                         ININSP/MAINT     1                      CA       23509                                                          DURING A VISUAL INSPECTION OF THE OTTER TIE BAR ASSEMBLY A LARGE COLLECTION OF DEAD FLY CARCASSES WERE FOUND CRAMMED INTO THE "U" CHANNEL SECTION OF THE TIE BAR.  ON FURTHER INVESTIGATION WITH THE BUG BIOMASS IT BECAME EVIDENT THAT THE BAR HAD STARTED TO EXFOLIATE.  THE TIE BAR ASSEMBLY WAS REPLACED.  A CONTRIBUTING FACTOR TO THE FAILURE MAY HAVE BEEN THE FACT THAT THE INSPECTION HOLES THAT WERE INCORPORATED TO INSPECT THE TIE BAR HAD NEVER BEEN ADEQUATELY RESEALED AFTER THE LAST INSPECTION.                                                                                                                                                                                                                                1H71 3R3  R  A815    5E2                  
20060705001542006070500154EA  2006       7          5          CA060321016      120060103G5312C3FS3413        BULKHEAD                                DHAV  DHC3  DHC3        2800202EA  PWA   R1340 R134059     52016NE                              FUSELAGE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       23509                                                          THE FOLLOWING FLOOR SUPPORTING STRUCTURE WAS FOUND TO BE UNSERVICEABLE IN THE CABIN AREA PN NR C3FS34-13 BULKHEAD LOWER STATION 133.33, C3FS13-27 BULKHEAD LOWER STATION 153.77, C3FS51-27 BULKHEAD LOWER STATION 174.2, C3FS58-15 BULKHEAD LOWER STATION 194.00 REPEATED HEAVY LOADS TO THE FLOOR AREA OVER 23'000 HRS HAD DAMAGED OR WEAKENED THE STRUCTURAL INTEGRITY OF THE FLOORBEAM ATTACH POINTS.  ALL OF THE TOP BULKHEAD FLANGES WERE DAMAGED AT THE INTERSECTION OF THE FLOORBEAMS REF #C3FS351-2.  THIS DEFECT IS ESPECIALLY IMPORTANT SINCE THE REAR CABIN SEAT/SEAT BELT RESTRAINT IS INDIRECTLY ATTACHED TO THE FLOOR BULKHEADS.                                                                                                  1H71 3R3  R  A815    5E2                  
20060705001582006070500158EA  2006       7          5          CA060321017      120060209G2730C3CF1267        HOUSING                                 DHAV  DHC3  DHC3        2800202EA  PWA   R1340 R134059     52016NE  HAMSTD23D   23D40       NE  ELEV QUADRANT   WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       23509                                                          THE ELEVATOR QUADRANT BEARING HOUSING WAS WORN BEYOND LIMITS AT THE BEARING ATTACH POINTS, REF NRB538.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3R3  R  A815    5E2     6  CP719     
20060705001592006070500159EA  2006       7          5          CA060322001      120060209G2720C3CF1277        HOUSING                                 DHAV  DHC3  DHC3        2800202EA  PWA   R1340 R134059     52016NE  HAMSTD23D   23D40       NE  RUDDER QUADRANT WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       23509                                                          THE RUDDER QUADRANT BEARING HOUSING WAS WORN BEYOND LIMITS AT THE BEARING ATTACH POINTS/PIVOT POINT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H71 3R3  R  A815    5E2     6  CP719     
20060705001642006070500164EA  2006       7          5          CA060322002      120060209G2750C3CF1073        FITTING                                 DHAV  DHC3  DHC3        2800202EA  PWA   R1340 R134059     52016NE  HAMSTD23D   23D40       NE  T/E FLAP        WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       23509                                                          BOTH INBOARD FLAP(C3CF104-5) TUBE END ASSEMBLIES (LT AND RT WINGS) C3CF107-3 WERE REPLACED DUE TO WEAR AND LOOSE ATTACH FASTENERS.  FAILURE OF THE PLUG END ON THE FLAP CONTROL TUBE COULD LEAD TO AN ASYMMETRIC FLAP CONDITION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1H71 3R3  R  A815    5E2     6  CP719     
20060627000832006062700083NE  2006       6          27         CA060322003      220060314G72406003T07G01      COMBUSTION CASE                         SKRSKYS61   S61L        8142102NE  GE    CT58  CT581401    30011NE                              ENGINE          CRACKED         W      O   OTHER                                                                                           J  WARNING INDICATION                                                            CRCRUISE         1                      CA            3356                          295269                      (CAN) THE PILOT NOTICED A GRADUALLY INCREASING ENGINE OIL PRESSURE, AND T5, ALONG WITH DECREASING OIL PRESSURE.  AFTER SHUTDOWN, THE ENGINE WAS INSPECTED, AND A CRACK FOUND IN THE LOWER COMBUSTION CASE HALF.  THE ENGINE WAS REMOVED FOR CASE REPLACEMENT AND TEST CELL RUN TO DETERMINE IF ALL INDICATIONS WERE A RESULT OF AIR LOSS THROUGH THE CASE CRACK. (TC NR 20060322003)                                                                                                                                                                                                                                                                                                                                                            2G72 4U4  U  1H15    1E3                  
20060705001702006070500170EU  2006       7          5          CA060322004      120060320G30205302412140      DEICE SYSTEM    PILATS      571101207   PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  INLET           CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       4720                                                           DURING MAINTENANCE OPERATION NOTICED EXHAUST SOOT TRAIL FROM INNER EDGE OF DEICE LIP ASSY.  REMOVAL OF DEICER LIP ASSY FROM COWL REVEALED A CRACK ON INNER PART OF LIP DEICE ON INLET SIDE.  DEICE LIP ASSY REPLACED WITH NEW.  P/N; OF CRACKED DEICE LIP ASSY IS 530.24.12.140.                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20060711001362006071100136CE  2006       7          11         CA060322006      120060316G2910991242322       VALVE                                   CESSNA525   525         2076601CE                                                               HYD SYSTEM      STUCK           W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA       3247                                                           LANDING GEAR DID NOT COME UP ON CLIMB.  PILOT FOUND COMPLETE FAILURE OF ALL HYDRAULIC SYSTEM.  ON TROUBLESHOOTING, FOUND SOLENOID LANDING VALVE SCREEN STUCK ON VALVE SEAT CAUSING COMPLETE BYPASS OF THE HYDRAULIC FLUID.  THIS VALVE WAS PLANNED TO BE REPLACED AT NEXT VISIT IAW SB 525-24-10.                                                                                                                                                                                                                                                                                                                                                                                                                                               1L72 4F    RTA1WI                         
20060711001592006071100159EA  2006       7          11         CA060322007      120060321G2797MS3476L2241S    CONNECTOR                               DHAV  DHC8  DHC8311     1386006EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF15      NE  ELEVATOR HEAT   BURNED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            CLCLIMB          1                      CA       3453834538                                                     (CAN) DURING CLIMB POSITION LT CIRCUIT BREAKER POPPED. MAINTENANCE TROUBLE SHOOTING FOUND REAR PRESSURE BULKHEAD (STA 708.45) PLUG CONNECTOR (9811-J9) TO HAVE SEVERAL BURNED PINS. ELEVATOR HORN HEAT , LOGO LIGHTS AND AFT POSITION LTS ARE ALL CONNECTED THRU THIS CONNECTOR PLUG. ELEVATOR HORN HEAT, POSITION LIGHTS , AND LOGO LIGHTS HAD REPORTED PREVIOUS INTERMITTANT FAULTS. CONNECTOR REPLACED AND TESTED SERVICEABLE. (TC NR 20060322007)                                                                                                                                                                                                                                                                                           2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060711001602006071100160WP  2006       7          11         CA060322008      120060320G8011BC3151002       STARTER                                 ROBSINR44   R44         7640120WP  LYC   O540  O540F1B5    41532EA                              ENGINE          MALFUNCTIONED   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            456                                                       (CAN) AIRCRAFT FAILED TO START. STARTER WAS REMOVED AND A OVERHAULED UNIT WAS INSTALLED AND NO FURTHER DEFECTS WERE NOTED. STARTER JUST COME OUT OF A REPAIR, 20.5 HRS EARLIER FOR INTERMITTENT/ERRATIC OPERATION. (TC NR 20060322008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1G71 3O3  O  H11NM   E295                 
20060626000012006062600001WP  2006       6          26         CA060322009      120060308G6322369D25623       BELT                                    HUGHES369   369D        4470706WP  ALLSN 250C  250C20B     03013GL                              BLOWER          FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       421                                                            (CAN) DURING A 100 HOUR INSPECTION THE BLOWER BELT WAS NOTED AS HAVING SEVERAL TEETH MISSING. BELT IS IDENTIFED WITH THE PN IN WHITE MARKER. BELT TENSION WAS VERIFIED AFTER INSTALLATION AND NO DEFECTS WERE NOTED DURING THE NEXT 3-100 HOUR INSPECTIONS. NO VIBRATIONS OR NOISE WERE NOTED. (TC NR 20060322009)                                                                                                                                                                                                                                                                                                                                                                                                                              1G71 3U3  U  H3WE    E4CE                 
20060710001042006071000104NE  2006       7          10         CA060322010      220060315G7321324485318       FUEL CONTROL                            DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF15      NE  ENGINE          LOOSE           W      O   OTHER                                                                                           J  WARNING INDICATION                                                            CRCRUISE         1                      CA       269831106                                                      DURING CRUISE PILOT REPORTED ENGINE PARAMETERS WANDERING.  NH +-0.4% NL +- 0.2%, RPM +- 2 .  MAINTENANCE INSPECTION FOUND POWER LEVERS ARMS LOOSE (LOW TORQUE/STILL COTTER PINNED ARMS RETIGHTEN AT ALL PIVOT POINTS AND RE-COTTER PINNED.  AIRCRAFT RETURNED TO SERVICE FUEL CONTROL UNIT HAD BEEN INSTALLED FOR 1106 HR/1331 CY.                                                                                                                                                                                                                                                                                                                                                                                                              2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060711001612006071100161EA  2006       7          11         CA060323001      220060131G74141068291013      HOUSING         BENDIX                  RKWELL700   700         7630520SW  LYC   O540  TIO540R2AD  41532EA  HARTZLHCE3Y HCE3YR2A    GL  MAGNETO         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            671   B101195                                             (CAN) DURING SCHEDULED MAINTENANCE, AN OIL LEAK WAS NOTED AT THE RT ENGINE MAGNETO GASKET. THE MAGNETO WAS REMOVED TO REPLACE A DEFECTIVE GASKET. UPON CLOSER INSPECTION A SMALL CRACK WAS FOUND ALONG THE MAGNETO MOUNTING FLANGE. OIL WAS SEEPING THROUGH THE CRACK. THE CRACK WAS HIDDEN BY THE MAGNETO RETAINING CLAMP, NUT AND LOCK WASHER.  (TC NR 20060323001)                                                                                                                                                                                                                                                                                                                                                                           1L72 3O3  O  A12SW   E14EA   5  CP33EA    
20060710001052006071000105NE  2006       7          10         CA060323002      220060311G85301830            CYLINDER                                DOUG  DC3   DC3CS1C3G   3021458WP  PWA   R1830 R183092     52020NE  HAMSTD23E   23E50       NE  NR 13           CRACKED         W      E   ENGINE SHUTDOWN                                                                                 E  VIBRATION/BUFFET                                                              CLCLIMB          1                      CA            422                           CP356035                    THE EXHAUST EAR OF NR 13 CYLINDER DEVELOPED A CRACK WHICH AFFECTED THE VALVE CLEARANCE OF THE EXHAUST VALVE, RESULTING IN A ROUGH RUNNING ENGINE.   CYLINDER ASSEMBLY WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4R4  R  A669    5E4     6  CP603     
20060623000022006062300002EU  2006       6          23         CA060323003      120060224G2930MS2771923       SWITCH                                  SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1        NE                              COLLECTIVE      MALFUNCTIONED   W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             NRNOT REPORTED   1                      CA                                                                      THE PILOT WAS CARRYING OUT HIS/HER PRE FLIGHT HYDRAULIC TEST "FAILED", HORN WAS UNABLE TO SOUND DUE TO FAULTY SWITCH.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1G71 3U3  U  H9EU    E19EU                
20060626000912006062600091CE  2006       6          26         CA060323004      120060323G7120                MOUNT                                   HELIO H250  H250        4300302CE                                                               ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      FWD FUSELAGE TUBING MOUNTING BOSSES FOR THE ENGINE MOUNT, AND THE L/H MAIN GEAR REAR ATTACH FITTING FOUND CRACKED DURING INSPECTION.  THE AREAS CRACKED WERE THE WELD JOINTS OF ALL 4 FWD FITTINGS AND THE INNER WELD JOINT ON THE LANDING GEAR FITTING.  ALL WELDS APPEAR TO BE FACTORY WELDS.  CAUSE OF FAILURE BELIEVED TO BE THAT WELD JOINTS WERE NOT PROPERLY NORMALIZED FROM FACTORY CAUSING BRITTLE REGIONS WITHIN THE WELDED AREA ITSELF.                                                                                                                                                                                                                                                                                              1H71 3O      1A8                          
20060710001062006071000106GL  2006       7          10         CA060324001      220060316G7200                ENGINE                                  CESSNA525   525         2076601CE  WILINTFJ44  FJ441A           GL                                              FAILED          W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         KEJFLUID LOSS                VIBRATION/BUFFET          WARNING INDICATION        CLCLIMB          1                      CA                                                                      DURING CLIMB-OUT, ENGINE BEGAN TO VIBRATE AND COMPRESSOR STALL.  OIL PRESSURE WENT TO ZERO.  PILOT PERFORMED SHUTDOWN AND RETURNED TO AIRPORT.  POST FLIGHT INSPECTION OF ENGINE REVEALED METAL ON CHIP COLLECTORS AND THE SPOOLS DID NOT TURN FREELY (BEARING NOISE).  THE MANUFACTURER WILL PROVIDE A TEARDOWN REPORT SOON.                                                                                                                                                                                                                                                                                                                                                                                                                   1L72 4F4  FRTA1WI    E3GL                 
20060710001072006071000107NM  2006       7          10         CA060324002      120060322G2897W1134360118     WIRE HARNESS                            BOEING737   737800*            NM  GE    CFM56 CFM56*      13802NE                              FUEL PUMP       DAMAGED         W      D   RETURN TO BLOCK                                                                                 J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      CA       3010                                                           A/C HAS NR 2 AFT FUEL PUMP LOW PRESSURE LIGHT ILLUMINATE ON TAXI.  A/C RETURNED TO GATE AND IT WAS DISCOVERED THAT ASSOCIATED CIRCUIT BREAKER WAS TRIPPED.  FURTHER INVESTIGATION REVEALED WIRE W1134-3601-18 HAD SHORTED TO GROUND.  MOC CONSULTED WITH BOEING ENGINEERING AND THE WIRE WAS TEMPORARILY REPAIRED IAW THE BOEING STANDARD WIRING PRACTICES MANUAL WITH A 10 DAY CONSTRAINT.  THE WIRE IS TO BE PERMANENTLY REPAIRED THIS WEEKEND.  THIS DEFECT HAS ALSO BEEN SUBMITTED TO THE BOEING FSE AS THIS IS AN IN SERVICE ISSUE.                                                                                                                                                                                                        2L72 4F4  FRTA16WE   E2GL                 
20060626000932006062600093NE  2006       6          26         CA060324003      220060324G73100301007710      LINE                                    SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1        NE                              FUEL SYS        BROKEN          W      O   OTHER                                                                                           KBJFLUID LOSS                SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION        TXTAXI/GRND HDL  1                      CA                                                                      A/C WOULD NOT START, FOUND LINE WAS BROKEN.  IF THE CONDITIONS WERE RIGHT A FIRE MAY HAVE OCCURRED ON START UP.  TURBOMECA HAS REPLACEMENT LINE WITH AN INCREASED DIAMETER AND WALL THICKNESS.  THE SB STATES, IN ORDER TO MINIMIZE THE POSSIBILITY OF THE PIPE RUPTURE DUE TO DISTORTION SB 292 73 0339 UPDATE 1.                                                                                                                                                                                                                                                                                                                                                                                                                              1G71 3U3  U  H9EU    E19EU                
20060626000942006062600094NE  2006       6          26         CA060324004      220060324G73100301007720      LINE                                    SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1        NE                              INJECTOR        BROKEN          W      O   OTHER                                                                                           KBJFLUID LOSS                SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION        TXTAXI/GRND HDL  1                      CA                                                                      THE PILOT WAS TRYING TO START THE ENGINE, IT WOULD NOT START.  UPON INSPECTION OF THE STARTING PROBLEM IT WAS FOUND THE THIS LINE WAS BROKEN.  TURBO MECA HAVE A REPLACEMENT LINE WITH AN INCREASED DIAMETER AND WALL THICKNESS.  THE SB IS RECOMMENDED/OPTIONAL. SB292 73 0339 UPDATE 1.                                                                                                                                                                                                                                                                                                                                                                                                                                                       1G71 3U3  U  H9EU    E19EU                
20060626000962006062600096EU  2006       6          26         CA060326001      120060325G6720704A34130184    CONTROL CABLE                           SNIAS 350   AS350BA     8680817EU  TMECA ARRIELARRIEL1B    6OO30NE                              TAIL ROTOR      UNSERVICEABLE   W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA                                                                      PILOT REPORTED T/R PEDALS FELT STICKY.  CABLE WAS INVESTIGATED AND FOUND STIFF AND ROUGH.  CABLE WAS CHANGED PROBLEM WAS SOLVED.  INSIDE CABLE MOISTURE AND CORROSION WERE FOUND.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1G71 3U3  UNCH9EU    E19EU                
20060710001082006071000108NM  2006       7          10         CA060327002      120060323G2780745583          SHAFT                                   DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  TE FLAPS        SEIZED          W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             LDLANDING        1                      CA                                                                      AFTER LANDING, THE PILOT WAS UNABLE TO RETRACT THE FLAPS. UPON INVESTIGATION BY MAINTENANCE, THE FLAP SECONDARY DRIVE CABLE WAS FOUND SIEZED (THE INNER CABLE HAD BROKEN STRANDS WHICH JAMMED THE CABLE).  THE SECONDARY DRIVE CABLE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                         2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060626000972006062600097EU  2006       6          26         CA060327003      120060324G3411                LINE                                    SOCATATBM   TBM700      8682000EU                                                               PITOT/STATIC SY CONTAMINATED    W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      DURING BIANNUAL ALTIMETER SYSTEM TEST AND INSPECTION PILOTS ALTIMETER AND VSI RESPONDED ERRATICALLY TO INCREASING/DECREASING PRESSURE.  WATER DROPLETS WERE FOUND IS PILOTS STATIC SYSTEM BETWEEN NR 1 LEFT STATIC VENT AND Y CONNECTION TO RIGHT VENT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L71 3T    RTA60EU                        
20060711001652006071100165CE  2006       7          11         CA060327004      120060321G322007436051        TORQUE LINK                             CESSNA182   182G        2072716CE  CONT  O470  O470R       17026SO  MCAULY2A36C 2A36C29     GL  NLG             CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3826                                                           (CAN) NOSE GEAR UPPER TORQUE LINK WAS FOUND CRACKED INSIDE UPPER CORNER ON THE LT SIDE.  FORGING NR 0543034-497, 2014 KAE-2A  (TC NR20060327004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1H71 3O3  ONT3A13    E273    5  CP880     
20060719000232006071900023CE  2006       7          19         CA060327005      120060324G3244650C063         TIRE                                    CESSNA425   425         2076018CE  PWA   PT6   PT6A112     52043NE  MCAULY4HFR344HFR34C762  NE  MLG             CUT             W      O   OTHER                                                                                           E  VIBRATION/BUFFET                                                              LDLANDING        1                      CA       103                                                            (CAN) LT MAIN TIRE POSSIBLE SIDEWALL PUNCTURE DURING LANDING ROLLOUT. NO OTHER DISCREPANCIES NOTED OTHER THAN DAMAGED SIDEWALL. NO DAMAGE TO AIRCRAFT OR OTHER COMPONENTS NOTED. (TC NR 20060327005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L72 3T3  TRTA7CE    E4EA    6  C3PNE     
20060719000242006071900024NE  2006       7          19         CA060328001      220060320G73220319878030      FCU                                     UROCOPEC120 EC120B      8680987EU  TMECA ARRIUSARRIU2F          NE                              ENGINE          LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       2891 68                            34096                       (CAN) DURING ROUTINE DAILY INSPECTION AFTER A FLIGHT, FUEL LEAK NOTICED AT THE MAIN FUEL OUTLET FITTING (NIPPLE) ON THE FCU. SUSPECT O-RING P/N 9794099203 DEFECTIVE. (TC NR 20060328001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1G72 3U3  UNCR0001RD E34NE                
20060719000252006071900025SO  2006       7          19         CA060328002      120060326G55141101411073004   CHANNEL                                 EMB   110   EMB110P1    3260122SO  PWA   PT6   PT6A34      52043EA  HARTZLHCB3T HCB3TN3     GL  HORIZONTAL STAB CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING COMPLETION OF A 6C INSP, MAINT FOUND A CRACK IN THE FWD LT HORIZONTAL STABILIZER MACHINED CHANNEL. THIS PARTICULAR INSP WAS COMPLETED DUE TO AD 83-03-03R6 REQUESTING AN INITIAL INSP AND MODIFICATION OF ATTACHMENT AREA. INITIAL REQUIREMENTS WERE PREVIOUSLY COMPLETED BY A PREVIOUS OPERATOR.  A REPEAT INSP IS NOW CALLED UP DURING 6C INSP AS REQUIRED BY AD.  CRACK WAS FOUND IN NEW MODEL OF MACHINED CHANNEL PART NR 110-4A-1411-07-16 THAT WAS PREVIOUSLY REPLACED. A VISUAL INSP OF ALL SURROUNDING AREA WAS COMPLETED AND AN EDDY CURRENT INSPECTION OF REMAINING FITTING WAS COMPLETED AND NO OTHER DISCREPANCY WAS FOUND.  CHANNEL WILL BE REPLACED AND AIRCRAFT WILL BE RETURNED TO SERVICE. (TC NR 20060328002)    1L72 4T4  T  A21SO   E4EA    6  CP15EA    
20060719000262006071900026EU  2006       7          19         CA060328004      120060327G3260C245890002      UPLOCK SWITCH                           AEROSPATR42 ATR42300    8680920EU  PWA   120   PW120            NE  HAMSTD14SF  14SF5       NE  MLG             FAILED          W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      CA                                                                      (CAN) DEPARTING, THE CREW OBSERVED AN UNSAFE(RED) WARNING ON NR 2 MAIN LANDING GEAR AFTER RETRACTION WAS SELECTED. THE CREW RETURNED TO POINT OF DEPARTURE AND AND CARRIED OUT A NORMAL CONFIGURATION LANDING. MAINTENANCE DETERMINED THAT THE UNSAFE CONDITION INDICATION WAS FALSE DUE TO A FAILED UPLOCK BOX. THE NR 2 MAIN GEAR UPLOCK BOX WAS REPLACED, TESTED SERVICEABLE AND AIRCRAFT RETURNED TO SERVICE.(TC NR 20060328004)                                                                                                                                                                                                                                                                                                            2H72 4T4  TRTA53EU   E20NE   6  CP7NE     
20060719000272006071900027SO  2006       7          19         CA060328005      120060321G7920PH481101        SEAL            CHAMPION                PIPER PA28  PA28140     7102802SO  LYC   O320  O320E3D     41508EA  SNSNCH74D   74DM        EA  OIL FILTER      COLLAPSED       W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       48                                                             (CAN) INTERNAL SEAL BETWEEN CARTRIDGE AND BASE PLATE COLLAPSED INTO CENTER OF FILTER.   (TC NR 20060328005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L71 3O3  O  2A13    E274    5  NP88614   
20060719000282006071900028EU  2006       7          19         CA060328006      120060323G56101379377C406     WINDOW                                  BAG   JETSTMJETSTM3212  1500217EU  GARRTTTPE331TPE33111U   01514WP  MCAULY4HFR344HFR34C652  NE  COCKPIT         CRACKED         W      B   EMER. DESCENT                                                                                   O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) DURING FLIGHT THE COPILOT WINDOW CRACKED, NO SOUND WAS HEARD. THE CAPTAIN IMMEDIATELY INITIATED DESCENT TO A SAFER LEVEL AND CONTINUED TO LAND.  THE WINDOW WAS FOUND TO BE CRACKED ON THE EXTERNAL LAYER WITH NO OBVIOUS INITIATING POINT AND REMOVED FROM THE AIRCRAFT.   (TC NR 20060328006)                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4T4  TRTBA15CAA E4WE    6  C3PNE     
20060719000292006071900029NM  2006       7          19         CA060328007      120060328G3350D71701100       BATTERY PACK                            BOEING737   737824      13844BZNM                                                               EMERGENCY LIGHT FAILED          W      K   NONE                                                                                            L  NO TEST                                                                       ININSP/MAINT     1                      CA                                                                      (CAN) PERFORMING EMERGENCY LIGHT AT L1,R1 AND R2 DOORS LIGHTS FAILED TO ILLUMINATE AT TEST THIS IS PART OF SERVICE CHECK  BATTERY PACK REPLACED (TC NR 20060328007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F    RTA16WE                        
20060626001002006062600100NE  2006       6          26         CA060328008      220060327G7314D7431           PUMP                                    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              FUEL SYS        FAILED          W      C   ABORTED TAKEOFF                                                                                 J  WARNING INDICATION                                                            TOTAKEOFF        1                      CA       599                                                            AS PILOT WAS READY FOR TAKEOFF, THE AUX PUMP LIGHT ILLUMINATED AND THE BREAKER POPPED.  PILOT LANDED AND NOTIFIED MAINTENANCE.  REPLACED THE PUMP ASSY.  THE PUMP ASSY ALSO HAS A WELDON PUMP P/N B8187-B S/N 105188.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1G71 3O3  O  H11NM   1E4                  
20060626001022006062600102CE  2006       6          26         CA060329001      120060321G3230                MOTOR                                   BEECH 200   B200        1152922CE  PWA   PT6   PT642A           NE  HARTZLHCB3T HCB3TN3     GL  MLG             FAILED          W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      AFTER TAKEOFF, EN ROUTE TO DESTINATION, GEAR WARNING LIGHT CAME ON.  PILOT TRIED EXTENDING THE GEAR AND NO EXTENSION WAS NOTED.  AIRCRAFT RETURNED TO BASE AND GEAR WAS EXTENDED USING MANUAL EXTENSION.  AIRCRAFT PUT ON LOCKS.  GEAR MOTOR CIRCUIT BREAKER WAS FOUND POPPED AND ACCUMULATOR WAS FOUND TO BE LOW IN PRESSURE.  CIRCUIT BREAKER WAS RESET AND ACCUMULATOR CHARGED TO PROPER PRESSURE.  GEAR SWUNG SEVERAL TIMES WITH NO ABNORMAL RESULTS.  AIRCRAFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                        1L72 4T4  T  A24CE   E4EA    6  CP15EA    
20060719000302006071900030NE  2006       7          19         CA060329002      220060327G8530                CYLINDER HEAD                           DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE  HARTZLHCB3R HCB3R304    GL  ENGINE          CRACKED         W      A   UNSCHED LANDING                                                                                 EBRVIBRATION/BUFFET          SMOKE/FUMES/ODORS/SPARKS  PARTIAL RPM/PWR LOSS      CLCLIMB          1                      CA            136                           2593                        (CAN) PILOT REPORTED JUST AFTER T/O, HEARD A POP AND THE ENGINE LOST A BIT OF POWER WITH SLIGHT VIBRATION. JUST AFTER THIS HE COULD SMELL A BIT OF BURNED OIL SMELL. AIRCRAFT RETURNED TO POINT OF DEPARTURE. INSPECTION INTO PROBLEM FOUND THAT NR 7 CYLINDER HAD SEPARATED BETWEEN HEAD AND BARREL. CYLINDER HAD 136.2 HRS SINCE OVERHAUL. ULTRASONIC INSPECTION OF CYLINDER IAW A/D 78-08-07 WAS CARRIED OUT AT OVERHAUL. CYLINDER ASSEMBLY WAS REPLACED AND AIRCRAFT WAS RETURNED TO SERVICE (TC NR 20060329002)                                                                                                                                                                                                                            1H71 3R3  RRCA806    5E1     5  CP28EA    
20060719000422006071900042CE  2006       7          19         CA060330001      120060329G323312802091        PIN             CESSNA                  CESSNA172   172RG       2072438CE  LYC   O360  O360F1A6    41514EA  MCAULY2D34C B2D34C220   GL  NLG ACTUATOR    CRACKED         W      O   OTHER                                                                                           J  WARNING INDICATION                                                            APAPPROACH       1                      CA       8274       2459                                                (CAN) NO GEAR DOWN INDICATION UNTILL RECYCLED SEVERAL TIMES. INSPECTION REVEALED CRACKED DOWNLOCK PIN (REF SEB 95-20)AND WORN ACTUATOR BEARING END PIN HOLE. (TC NR 20060330001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1H71 3O3  O  3A17    E286    5  CP7EA     
20060626001082006062600108    2006       6          26         CA060330002      120060330G2824AVZ4B11198      VALVE                                                                                                                                   FUEL SYSTEM     DAMAGED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      ELECTRIC MOTOR SECTION OF PUMP ASSY WAS FOUND DURING INSPECTION TO MISSING A "C" CLIP AND PLUG.  REPLACED WITH SERVICABLE UNIT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           
20060720003202006072000320NM  2006       7          20         CA060330003      120060330G6330500N3139        MOUNT                                   DOUG  600N  600N        3027377NM                                                               GEARBOX         CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) CRACKS WERE FOUND IN THE MOUNT IS SIMILAR LOCATION ON 2 COMPANY AIRCRAFT. (TC NR 20060330003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1G71 3U    NCH3WE                         
20060719000542006071900054CE  2006       7          19         CA060330004      120060326G27517013348931      INDICATOR                               LEAR  45    45LEAR      5170805CE  GARRTTTFE731TFE7312     01518WP                              TE FLAPS        FAILED          W      L   ABORTED APPROACH                                                                                P  NO WARNING INDICATION                                                         APAPPROACH       1                      CA            1333                                                      (CAN) ON APPROACH, CREW NOTICED THAT AFTER FLAP WAS SELECTED LT FLAP INDICATION MOVED NORMALLY WHERE RT FLAP INDICATION REMAINS AT ZERO DEGREES POSITION. CREW DID NOT FEEL ANY FLAP ASSYMETRY. AC DID NOT REGISTER A FLAP ASSYMETRY, DID NOT PROVIDE A FLAP FAIL CAS MESSAGE. CREW NOTED THIS AS AN INDICATION PROBLEM ONLY. MAINT TROUBLESHOT SYS AND CONFIRMED IT TO BE AN INDICATION PROBLEM ONLY, REASON WHY AC DID NOT PROVIDE A FLAP FAIL CAS MESSAGE. FURTHER TROUBLESHOOTING DISCOVER INDICATION PROBLEM TO BE CAUSED BY RT DATA ACQUISITION UNIT, PORTION OF FLAP POSITION ON CHANNEL (B) HAD FAILED  AT ZERO DEGREES POSITION.  A REPAIRED DAU WAS INSTALLED AND AC WAS RETURNED TO SERVICE. (TC NR 20060330004)                     2L72 4F4  FRTT00008WIE6WE                 
20060719000552006071900055EA  2006       7          19         CA060330005      120060330G7120C6WM151928      MOUNT                                   DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A27      52043EA  HARTZLHCB3T HCB3TN3     GL  ENGINE          MISMANUFACTURED W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA                                          18503587                    (CAN) ENGINE MOUNT PLATE INCORRECTLY MANUFACTURED. THE HOLE FOR THE ENGINE MOUNT BOLT (MS21250-06042) IS NOT DRILLED AT THE CORRECT ANGLE. THE HOLE FROM THE MOUNT PLATE TO THE FITTING, ENGINE MOUNT P/N C6WM 1517-28 DOES NOT LINE UP.  MARKINGS ON THE PLATE ARE, P/N C6WM 1519-28, W/O14947/1 AND AUG 12/04.  (TC NR 20060330005)                                                                                                                                                                                                                                                                                                                                                                                                           1H72 3T4  TRTA9EA    E4EA    6  CP15EA    
20060719000562006071900056EA  2006       7          19         CA060330006      120060330G28102156400         FUEL CELL                               CNDAIRCL215 CL2156B11215       EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  RT WING         LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       1318                                                           (CAN) DURING INSPECTION FOR A FUEL LEAK OF THE RT WING. ALL CELLS WERE REMOVED FOR LEAK CHECK. CELLS  NR 1,2,4,6 AND 7 WERE FOUND LEAKING. CELLS WILL BE REPLACED. (TC NR 20060330006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2H72 4T4  TRTA14EA   E20NE   6  CP7NE     
20060719000572006071900057NM  2006       7          19         CA060330007      120060330G2997SM601BA20A1     CONTACTOR                               DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  HYD CIRCUIT BRKRSTUCK           W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA                                                                      (CAN) AFTER TAKE-OFF THE PILOTS WERE COMPLETING THE AFTER TAKE-OFF CHECKS AND THEY NOTICED THAT THE NR 2 HYDRAULIC STANDBY POWER UNIT WAS INDICATING PRESSURE EVEN WITH THE SPU SELECTED OFF. THE PILOTS ELECTED TO RETURN TO BASE FOR FURTHER INVESTIGATION. THE MAINTENACE STAFF FOUND THAT THE HYDRAULIC REMOTE CIRCUIT BREAKER CONTACTOR WAS STUCK IN THE ON POSITION. CONTACTOR WAS REPLACED AND AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060330007)                                                                                                                                                                                                                                                                                     2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060626001092006062600109WP  2006       6          26         CA060331001      120060330G6510C0411           BEARING         ROBSIN                  ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              T/ROTOR DRIVE   SPUN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       198        0678                                                DURING INSPECTION IT WAS NOTED THAT THE T/R D/S ASSY BEARING HAD SPUN.  THE INNER RACE ROTATED ON SHAFT ROTATED 1/4 TURN AND WITNESSED BY TORQUE SEAL.  DRIVESHAFT REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1G71 3O3  O  H11NM   1E4                  
20060719000582006071900058NE  2006       7          19         CA060331002      220060329G73130301007720      INJECTOR                                SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1        NE                              FUEL SYSTEM     CRACKED         W      K   NONE                                                                                            J  WARNING INDICATION                                                            ININSP/MAINT     1                      CA                                          10205                       (CAN) UPON LANDING AT A MOUNTAIN TOP (6000 FT) ASL. PILOT UNABLE TO COMPLETE ENGINE START. AFTER ARRIVAL OF AME IS HAS BEEN DISCOVERED THAT RT FUEL INJECTOR PIPE WAS CRACKED AROUND ENTIRE CIRCUMFERENCE AT THE FLARE END.  PIPE SUBSEQUENTLY REPLACED WITH SERVICEABLE.  A/C RETURNED TO SERVICE.  (TC NR 20060331002)                                                                                                                                                                                                                                                                                                                                                                                                                        1G71 3U3  U  H9EU    E19EU                
20060626001112006062600111    2006       6          26         CA060331003      420060331G2562                G SWITCH        POINTER     PS400010    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              ELT             WEAK            W      K   NONE                                                                                            L  NO TEST                                                                       ININSP/MAINT     1                      CA                  409070                                              ELT WAS BEING RECERTIFIED AND TESTED IN-HOUSE.  THE G SWITCH WAS FOUND WEAK.  ELT WAS RETURNED TO POINTER FOR FURTHER REPAIR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1G71 3O3  O  H11NM   1E4                  
20060719000592006071900059    2006       7          19         CA060331004      220060331G7261CH481101        OIL FILTER                                                                                                                              ENGINE          DAMAGED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) UPON RECEIPT OF NEW OIL FILTER, THREADS WERE FOUND TO BE GALLED. (TC NR 20060331004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                
20060626001122006062600112SW  2006       6          26         CA060331005      120060327G3246                SADDLE                                  BELL  205   205A1       1181414SW  LYC   T53   T5317A      41549NE                              SKID TUBE       CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      CRACK WAS FOUND ON SKID TUBE AT FORWARD CROSSTUBE MOUNTING SADDLE.  THERE WAS NO REPORT OF A HARD LANDING WITH THIS AIRCRAFT AT THIS TIME.  TIMES FOR THESE SKID TUBES WERE NOT AVAILABLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 4U4  U  H1SW    E17EA                
20060626001132006062600113CE  2006       6          26         CA060402001      120060327G553211564000098     SKIN                                    BEECH 100   100BEECH    1152916CE  PWA   PT6   PT6A28           EA                              VERTICLE STAB TECRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      TRAILING EDGE SKIN, RT SIDE CRACKED APPROX 1 INCH AT MAIN SPAR STATION.  CRACK STARTS AT ONE JO BOLT FASTENER LOCATION AND GOES DOWN TO EDGE OF SKIN.  MOST OF THE CRACK WAS HIDDEN BY THE LOWER RIGHT STABILIZER ATTACH/FAIRING ANGLE P/N 97-440025-14.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L72 3T4  T  A14CE   E4EA                 
20060719000602006071900060EA  2006       7          19         CA060403001      120060328G5610NP13932113      WINDSHIELD                              CNDAIRCL600 CL6002C10   1390015EA  GE    CF34  CF348C1          NE                              COCKPIT         BROKEN          W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) ENROUTE THE OUTER PLY PILOT WINDSHIELD SHATTERED AND IMPAIRED CAPT'S VIEW . A/C DIVERTED  WINDSHIELD REPLACED, AIRCRAFT DECLARED SERVICEABLE. (TC NR 20060403001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRTA21EA   EOOO63EN             
20060626001142006062600114SW  2006       6          26         CA060403002      120060330G6210STC             WIRE STRIKE                             BELL  427   427         1182207SW  PWC   PW207 PW207D           NE                                              DAMAGED         W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             TXTAXI/GRND HDL  1                      CA       539                                                            DURING COOL DOWN AT IDLE RPM CYCLIC CONTROL STICK WAS MOVED FORWARD AND MAIN ROTOR BLADE (QTY 2) CONTACTED THE UPPER CUTTER OF THE WIRE STIKE PROTECTION SYSTEM.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1G71 3U3  U  R00001RCE42NE                
20060719000612006071900061EA  2006       7          19         CA060403003      120060219G21331036322         OUTFLOW VALVE                           CNDAIRCL604 CL604       1900301EA                                                               CABIN PRESSURE  FAILED          W      O   OTHER                                                                                           G  MULTIPLE FAILURE                                                              CLCLIMB          1                      CA                                                                      (CAN) ON A FLIGHT DURING CLIMB OUT AT FL 110 AND CLEARED FOR FL150 A (CABIN ALT) EICAS MESSAGE POSTED. THE CREW OBSERVED THAT CABIN ALTITUDE WAS CLIMBING IN AN UNUSUAL HIGH RATE. WHEN CABIN ALTITUDE REACHED 10000 FEET CREW DECIDED TO CONTROL IN MANUAL MODE. NO RESPONSED WAS NOTED. NOW GOR A MASTER WARNING DUE TO CABIN ALTITUDE HIGHER THAN 10000 FEET AND O2 MASKS DROPPED AND CREW PUT THEIR OWN MASKS ON. CREW DECIDED TO LEVEL OFF AT 15000 FEET AND FERRY FLOWN THE AIRCRAFT AT LOW LEVEL. ALSO OUTFLOW VALVE P/N 103664-2 WAS REPLACED AS BOTH VALVES FAILED THE TO PASS THE AMM TESTING. (TC NR 20060403003)                                                                                                                    2L72 4F    RTA21EA                        
20060719000622006071900062EA  2006       7          19         CA060403004      120060305G2820601R626765      SHROUD                                  CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              COLLECTOR BOX   FAILED          W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) DURING A POST HEAVY CHECK INSPECTION IT WAS DISCOVERED THAT A FUEL LEAK COMING OFF THE FUSELAGE DRAINS AT STATION 559.00 AND 574.00. AFTER INVESTIGATION, IT WAS DETERMINED THAT THE FUEL LEAK WAS COMING FROM THE FUEL COLLECTOR BOX SHROUD (P/N 601R62676-5). A BRACKET INSIDE THE COLLECTOR BOX IS BROKEN AND CHAFED ON THE LT ENGINE FEED LINE. THE AIRCRAFT IS CURRENTLY DOWN AND AWAITING PARTS (TC NR 20060403004)                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA21EA   E15NE                
20060719000632006071900063NE  2006       7          19         CA060403005      220060302G7200                ENGINE                                                                     PWA   PT6   PT6A67R     52043NE                                              MAKING METAL    W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                          106004                      (CAN) IN FLIGHT, THE ENGINE LOW OIL PRESSURE WARNING ANNUNCIATED AND  THE ENGINE WAS SHUTDOWN.  SUBSEQUENT INSPECTION REVEALED METALIC DEBRIS IN THE ENGINE OIL.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE EXTABLISHED. (TC NR 20060403005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        4  T          E26NE                
20060719000642006071900064NE  2006       7          19         CA060403006      220060305G7200                ENGINE                                  CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE                                              FLAMED OUT      W      A   UNSCHED LANDING                                                                                 XJ ENGINE FLAMEOUT           WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) INFLIGHT THE ENGINE EMITTED A LOUD NOISE, INTERTURBINE TEMPERATURE INCREASED AND THE ENGINE FLAMED OUT.  A DEAD-STICK LANDING WAS CARRIED OUT RESULTING IN SIGNIFICANT AIRCRAFT DAMAGE.  MFG WILL INVESTIGATE AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060403006)                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3T3  T  A37CE   E4EA                 
20060613002502006061300250NE  2006       6          13         CA060403007      220060220G7314                PUMP                                    BEECH 200   200BEECH    1152920CE  PWA   PT6   PT642A           NE                              FUEL SYS        UNSERVICEABLE   W      O   OTHER                                                                                           XJ ENGINE FLAMEOUT           WARNING INDICATION                                  DEDESCENT        1                      CA                                                                      ON DESCENT, THE ENGINE EXPERIENCED AN UNCOMMANDED SHUTDOWN.  THE FUEL CONTROL UNIT AND FUEL PUMP WERE SUBSEQUENTLY REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L72 4T4  T  A24CE   E4EA                 
20060606002262006060600226NE  2006       6          6          CA060403008      220060112G7314                SPLINE                                  BEECH 45    T34C        1152015CE  PWA   PT6   PT6A25      52043NE                              FUEL PUMP       WORN            W      K   NONE                                                                                            R  PARTIAL RPM/PWR LOSS                                                          NRNOT REPORTED   1                      CA                                                                      THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION WHICH RESULTED IN THE AIRCRAFT CRASHING.  INVESTIGATION DETERMINED THE FUEL PUMP SPLINE TO BE SUFFICIENTLY WORN TO RESULT IN THE LOSS OF ENGINE FUEL FLOW.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L71 3T3  T  A26CE   E4EA                 
20060607002522006060700252NE  2006       6          7          CA060403009      220060309G7200                ENGINE          PWC         PT6A114A    CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE                              ENGINE          POWER LOSS      W      O   OTHER                                                                                           R  PARTIAL RPM/PWR LOSS                                                          CLCLIMB          1                      CA                  PC0624                                              DURING CLIMB, THE ENGINE EXPERIENCED AN UNCOMMANDED LOSS OF POWER.  THE AIRCRAFT CRASHED ON ATTEMPTING TO RETURN TO POINT OF DEPARTURE.  P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1H71 3T3  T  A37CE   E4EA                 
20060607002532006060700253GL  2006       6          7          CA060403010      220060326G7230                TUBE            RROYCE      6896024CP   BELL  206   206L1       1182107SW  ALLSN 250C  250C28B     03013GL                              ENGINE          BROKEN          W      BE  EMER. DESCENT           ENGINE SHUTDOWN                                                         CERF.O.D.                    VIBRATION/BUFFET          PARTIAL RPM/PWR LOSS      TOTAKEOFF        1                      CA                                                                      PILOT HEARD A BIG "BANG" FROM ENGINE AND LOST POWER.  THE PILOT LANDED IN THE BUSH WITHOUT DAMAGING THE A/C.  AFTER THE INSPECTION OF THE COMPRESSOR BY THE MECHANIC, FOUND THE COMPRESSOR IN BAD SHAPE, CONFIRMED FOD WAS IN TO THE COMPRESSOR.  MECHANIC CHECKED AND FOUND SOME LITTLE METAL PIECES IN THE INTAKE BEHIND THE INLET SCREEN, FINALLY FOUND THE INJECTOR TUBE BROKEN ON THE WELDING POINT.                                                                                                                                                                                                                                                                                                                                       1G71 3U3  U  H2SW    E1GL                 
20060607002542006060700254NE  2006       6          7          CA060403011      220060305G7200                ENGINE          PWC         PT6A114A    CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE                              ENGINE          POWER LOSS      W      A   UNSCHED LANDING                                                                                 EX VIBRATION/BUFFET          ENGINE FLAMEOUT                                     NRNOT REPORTED   1                      CA                  PC0717                                              THE ENGINE EMITTED A LOUD NOISE FOLLOWED BY AN UNCOMMANDED INFLIGHT SHUTDOWN.  THE AIRCRAFT DEPARTED THE RUNWAY ON LANDING RESULTING IN SIGNIFICANT AIRFRAME DAMAGE.  P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H71 3T3  T  A37CE   E4EA                 
20060607002552006060700255EA  2006       6          7          CA060403012      220060310G7532                BLEED VALVE     PWC         310082903   DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A27      52043EA                              COMPRESSOR      FAULTY          W      E   ENGINE SHUTDOWN                                                                                 ER VIBRATION/BUFFET          PARTIAL RPM/PWR LOSS                                APAPPROACH       1                      CA                                                                      DURING APPROACH, THE ENGINE EMITTED AN UNUSUAL NOISE FOLLOWED BY AN UNCOMMANDED POWER REDUCTION.  THE ENGINE WAS SHUT DOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED A FAULTY COMPRESSOR BLEED VALVE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H72 3T4  TRTA9EA    E4EA                 
20060607002562006060700256NE  2006       6          7          CA060403013      220060315G7200                ENGINE          PWC         PT6A42      BEECH 200   200BEECH    1152920CE  PWA   PT6   PT642A           NE                              ENGINE          POWER LOSS      W      A   UNSCHED LANDING                                                                                 X  ENGINE FLAMEOUT                                                               CRCRUISE         1                      CA                  94570                                               (CAN) DURING CRUISE THE ENGINE EXPERIENCED AN UNCOMMANDED SHUT DOWN.  THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  P&WC WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L72 4T4  T  A24CE   E4EA                 
20060607002572006060700257GL  2006       6          7          CA060403014      320060316G6110                SEAL                                    BEECH 90    C90A        1152911CE  PWA   PT6   PT6A21      52043EA  HARTZLHCB3T HCB3TN3     GL  PROPELLER       LEAKING         W      E   ENGINE SHUTDOWN                                                                                 K  FLUID LOSS                                                                    CRCRUISE         1                      CA                                                                      DURING FLIGHT, AN ENGINE OIL LEAK WAS OBSERVED AND THE ENGINE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED A LEAKING PROPELLER SHAFT SEAL AND A LOOSE BETA VALVE RETAINING NUT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L72 3T4  TRT3A20    E4EA    6  CP15EA    
20060607002582006060700258NE  2006       6          7          CA060403015      220060316G7320                FUEL SYS        PWC         PT6A42      BEECH 200   B200        1152922CE  PWA   PT6   PT642A           NE                              ENGINE          FLUCTUATES      W      E   ENGINE SHUTDOWN                                                                                 M  OVER TEMP                                                                     DEDESCENT        1                      CA                  94383                                               DURING INITIAL DESCENT, ENGINE FUEL FLOW WAS OBSERVED TO FLUCTUATE.  THROTTLE INPUT RESULTED IN EXCESSIVE INTERTURBINE TEMPERATURE INCREASE AND THE ENGINE WAS SHUT DOWN IN FLIGHT.  P&WC WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L72 4T4  T  A24CE   E4EA                 
20060619001792006061900179NE  2006       6          19         CA060403016      220060323G7200                ENGINE                                  GULSTM200   200         4500308NM  PWA   306   PW306B           NE                                              MAKING METAL    W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      CA                                          CC0095                      (CAN) DURING CLIMB, THE ENGINE EMITTED A LOUD NOISE FOLLOWED BY AN UNCOMMANDED POWER REDUCTION.  THE ENGINE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED METAL DEBRIS IN THE ENGINE EXHAUST.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060403016)                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA53NM   E35NE                
20060607002592006060700259NE  2006       6          7          CA060403017      220060321G7200                ENGINE          PWC         PW123D      DHAV  DHC8  DHC8*              NM  PWA   120   PW123D      52152NE  HAMSTD14SF  14SF23      NE  ENGINE          POWER LOSS      W      A   UNSCHED LANDING                                                                                 EJXVIBRATION/BUFFET          WARNING INDICATION        ENGINE FLAMEOUT           CRCRUISE         1                      CA                  AT0009                                              DURING CRUISE, THE ENGINE EMITTED A LOUD NOISE FOLLOWED BY A LOW ENGINE OIL PRESSURE INDICATION AND AN UNCOMMANDED ENGINE SHUT DOWN.  SUBSEQUENT INSPECTION REVEALED METAL CONTAMINATION AND A SEIZED COMPRESSOR.  P&WC WILL MONITOR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED.                                                                                                                                                                                                                                                                                                                                                                                                                                       2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060607002602006060700260EU  2006       6          7          CA060403018      120060329G7931                OIL SYSTEM      PWC         PW127E      AEROSPATR42 ATR42500    8680948EU  PWA   PW120 PW127            NE                              ENGINE          LOW PRESSURE    W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                  127187                                              DURING CLIMB, ENGINE OIL PRESSURE WAS OBSERVED TO FLUCTUATE FOLLOWED BY A LOSS OF OIL PRESSURE.  THE ENGINE WAS SHUT DOWN IN FLIGHT.  P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2H72 4T4  TRTA53EU   E20NE                
20060608002222006060800222EA  2006       6          8          CA060403019      220060429G7200                ENGINE                                  BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA                                              FAILED          W      O   OTHER                                                                                           XJ ENGINE FLAMEOUT           WARNING INDICATION                                  NRNOT REPORTED   1                      CA                                                                      THE ENGINE WAS REPORTED TO HAVE EXPERIENCED AN INFLIGHT SHUTDOWN.  SUBSEQUENT INSPECTION REVEALED METAL DEBRIS ON THE ENGINE CHIP DETECTOR.  P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L72 4T4  T  A24CE   E4EA                 
20060608002852006060800285EA  2006       6          8          CA060403020      120060402G2910MS21907D6       ELBOW                                   CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30015NE                              HYD SYSTEM      SPLIT           W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      45 DEGREE UNIVERSAL ELBOW FITTING FOUND SPLIT WITH HYDRAULIC FLUID LEAKAGE ON THE NR 2 HYDRAULIC SYSTEM, IPC 29-11-00, FIG 20, VIEW K, ITEM NR 45.  FITTING REPLACED WITH THE SYSTEM CHECKED SERVICEABLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F4  FRTA21EA   E15NE                
20060612003432006061200343EA  2006       6          12         CA060403021      120060403G3246AJ78241         TUBE                                    DHAV  DHC3  DHC3        2800202EA                                                               MLG             CRACKED         W      O   OTHER                                                                                           J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      AFT LT STRUT TUBE CRACKED PN AJ78-24-1.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1H71 3R      A815                         
20060612003452006061200345EA  2006       6          12         CA060403022      120060403G3246J78221          STRUT                                   DHAV  DHC3  DHC3        2800202EA                                                               MLG             CRACKED         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA                                                                      AFT LT STRUT CLEVIS CRACKED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H71 3R      A815                         
20060612003462006061200346EA  2006       6          12         CA060403023      120060403G3246AJ78211         CLEVIS                                  DHAV  DHC3  DHC3        2800202EA                                                               MLG             CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         CLCLIMB          1                      CA                                                                      AFT RT SPREADER CLEVIS CRACKED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1H71 3R      A815                         
20060612003482006061200348EA  2006       6          12         CA060403024      120060403G3246J781112         PLATE                                   DHAV  DHC3  DHC3        2800202EA                                                               FLOAT           CORRODED        W      O   OTHER                                                                                           O  OTHER                                                                         CLCLIMB          1                      CA                                                                      SEVERE CORROSION ON FWD AND AFT FLOAT BUILD-UP ESPECIALLY LOWER SURFACES OF P/N J78-11, J78-12.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1H71 3R      A815                         
20060612003492006061200349EA  2006       6          12         CA060403025      120060403G3246J7819           CLEVIS                                  DHAV  DHC3  DHC3        2800202EA                                                                               DAMAGED         W      O   OTHER                                                                                           O  OTHER                                                                         CLCLIMB          1                      CA                                                                      J78-19 CLEVIS, RT AND LT FRONT STRUT LOWER.  HOLE IN FITTING FILLED WITH ROD, HOLE MOVED AND LIKELY IN A NON-COMPLIANT MANNER DURING MFG.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3R      A815                         
20060626001152006062600115WP  2006       6          26         CA060403026      120060403G2910D4523           B-NUT                                   ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              HYD SYSTEM      LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       398                                                            HYDRAULIC FLUID LEAKING FROM FITTING.  BACKUP NUT ON FITTING FOUND UNDER TORQUED.  FACTORY TORQUE SEAL AND PAL NUT WERE FOUND UNDISTURBED.  BACKUP NUT RETORQUED AND NO FURTHER DEFECTS FOUND.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1G71 3O3  O  H11NM   1E4                  
20060626001172006062600117NE  2006       6          26         CA060403028      220060401G73147436024         FUEL CONTROL                            BOEING727   727225      1384077NM  PWA   JT8   JT8D9A      52048NE                              NR 2 ENGINE     MALFUNCTIONED   W      E   ENGINE SHUTDOWN                                                                                 RXJPARTIAL RPM/PWR LOSS      ENGINE FLAMEOUT           WARNING INDICATION        CRCRUISE         1                      CA                                          666126                      AT CRUISE ALTITUDE(FL350), THE NR 2 ENGINE WAS SURGING AND DROPPING POWER. ENGINE ANTI ICE AND FUEL HEAT CHECK C/W, NO CHANGE, ENGINE FAILURE- SHUTDOWN CHECK LIST C/W, NR 2 ENGINE SHUTDOWN INFLIGHT.  MAINTENANCE INSPECTED AIRCRAFT IAW PW MM 72-00-00 PAGE 531.  ENGINE FUEL PUMP/FCU PACKAGE REPLACED AND AIRCRAFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                    2L73 4F4  F  A3WE    E2EA                 
20060612003502006061200350EA  2006       6          12         CA060403029      120060403G5210C3FS24950       DOOR                                    DHAV  DHC3  DHC3        2800202EA                                                               FUSELAGE        CORRODED        W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      THE LT STRUT, FUSELAGE DOOR WAS CORRODED THROUGH.  SURFACE RUST PITTING WAS NOTICED, AND A PUNCH WAS DRIVEN THROUGH THE TUBE WITH MINIMAL EFFORT SEVERAL TIMES.  RT STRUT EXHIBITED SEVERE PITTING ALSO, AND WAS ALSO REMOVED FOR REPLACEMENT.  LOGBOOKS INDICATED THAT THE STRUTS WERE INSPECTED AUG 20, 2001 IAW S/B 3/29 BY AMO 78-92.                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3R      A815                         
20060612003512006061200351CE  2006       6          12         CA060404001      120060403G3411MILH55934       HOSE                                    LEAR  35    35A         5170602CE  GARRTTTFE731TFE73122B   01518WP                              RT PITOT/STATIC CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1975                                                           DURING A SCHEDULED INSPECTION, THE AVIONICS TECHNICIAN VISUALLY DISCOVERED SEVERAL HOSES CRACKED IN THE RT PITOT/STATIC CIRCUIT.  HOSES WERE FOUND CRACKED AND LEAKING ON THE LT PITOT/STATIC CIRCUIT APPROXIMATELY 1 MONTH AGO.  THESE PARTICULAR HOSES WERE INSTALLED FOR RVSM CONVERSION.                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F4  F  A10CE   E6WE                 
20060612003522006061200352EU  2006       6          12         CA060404002      120060329G2800L95F50603       DISK                                    AIRBUSA321  A321211     3930370EU                                                               CENTER TANK     RUPTURED        W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA                                                                      FUEL AUTO TRANSFER FAULT ECAM IN CLIMB.  SELECTED MAN AS PER ECAM.  REALIZED NR 1 TANK WAS FEEDING BOTH ENG AND UNBALANCE INCREASED.  UNABLE TO GET FUEL FROM CENTER OR RIGHT TANK.  RETURNED TO YYZ.   RECTIFICATION: TSM TASK 28-12-00-810-801 CARRIED OUT.  OVERPRESSURE PROTECTOR DISK 96QM RUPTURED.  REMOVED TASK 28-12-41-000-003 AND INSTALLED TASK 28-12-41-400-003 MM TASK 28-25-00-869-001 FUEL TRANSFER AND PANEL LEAK CHECK CARRIED OUT SERVICEABLE.                                                                                                                                                                                                                                                                               2L72 4F    RTA28NM                        
20060613000452006061300045    2006       6          13         CA060404003      420060329G2330845438421       VIDEO DISPLAY                           AIRBUSA340  A340313            EU  CFMINTCFM56 CFM565C4    13802NE                              CABIN           BURNED          W      H   DEACTIVATE SYST/CIRCUITS                                                                        B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA                                                                      4H VIDEO MACHINE GOT REALLY HOT AND SMELLED BURNED AT THE END OF FLIGHT.  THICK WHITE SMOKE CAME FROM PTV.  FOUND PTV OPERATION SERV.  FOUND SEAT PWR SUPPLY U/S AND ODOR OF SMOKE.  DEACTIVATED BY PULLING AND COLLERING C/B.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L74 4F4  FRTA197    E37NE                
20060613001702006061300170NM  2006       6          13         CA060404004      120060314G32402445901         DISC            BFGOODRICH              DHAV  DHC8  DHC8202     2809007NM  PWA   120   PW123D      52152NE  HAMSTD14SF  14SF23      NE  RT MLG BRAKE    DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            435   0279                                                DURING BRAKE ASSY OVERHAUL THE TECHNICIAN DISCOVERED THE ROTATING DISC WAS BADLY DAMAGED.  AFTER FURTHER INVESTIGATION, IT WAS FOUND THAT THE KEYWAYS ON THE WHEEL ASSEMBLY WERE MISALIGNED ON THE BRAKE DISC DURING INSTALLATION.  THE BRAKE ASSY WAS INSPECTED DURING OVERHAUL WITH NO DAMAGE FOUND ON IT.  THE WHEEL ASSY WAS ALSO REPLACED AND SENT FOR NDT ALSO WITH NO DAMAGE FOUND ON IT.  THE ONLY ITEM THAT WAS REPLACED ON THE WHEEL ASSY WERE THE KEYWAYS P/N 170-209-2.  THE ROTATING DISC P/N 244-590-1 WAS REPLACED AND AIRCRAFT FOUND SERVICEABLE.                                                                                                                                                                               2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060626001182006062600118SO  2006       6          26         CA060404005      120060403G2497                WIRE                                    PIPER PA31T PA31T       7103124SO  PWA   PT6   PT6A28           EA  HARTZLHCB3T HCB3TN3     GL  DC REGULATOR    BROKEN          W      H   DEACTIVATE SYST/CIRCUITS                                                                        J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      IN CRUISE, PILOT NOTICED THAT THE RIGHT GENERATOR ANNUNCIATOR WAS ON AND THERE WAS NO INDICATION ON THE RIGHT AMMETER.  THE GENERATOR WOULD NOT COME ONLINE AND THE GENERATOR WAS SWITCHED OFF.  THERE WAS NO FURTHER EVENTS AND THE AIRCRAFT LANDED WITHOUT INCIDENT.  AFTER EXTENSIVE TROUBLESHOOTING, A BROKEN WIRE WAS DISCOVERED OFF THE RIGHT OVERLOAD SENSOR.  THE WIRE WAS REPAIRED AND SYSTEM TESTED SERVICEABLE.                                                                                                                                                                                                                                                                                                                      1L72 3T4  T  A8EA    E4EA    6  CP15EA    
20060613001712006061300171EA  2006       6          13         CA060404006      120060323G5551600230681       BUSHING                                 CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30015NE                              HORIZONTAL STAB WORN            W      O   OTHER                                                                                           E  VIBRATION/BUFFET                                                              CLCLIMB          1                      CA       2478924789                                                     ON DEPARTURE (200 KTS GEAR UP FLAPS 0), A LOW FREQUENCY VIBRATION WAS FELT THROUGH THE AIRCRAFT, BOTH FLIGHT DECK AND CABIN.  VIBRATION WAS NOTICEABLE ENOUGH TO SHAKE SEATS SIDE TO SIDE, ENGINE FAN VIBRATION 0.2 AND 0.5, SMOOTH AIR FLIGHT CONDITIONS.  CHECKED COMPLETE AIRCRAFT AND FOUND ALL FOUR HORIZONTAL STABILIZER BUSHINGS (WHICH HOLD STAB ON) SLIGHTLY WORN.  BUSHING REPLACED AS PER SB 601R-55-007 PARTS A & B ONLY.  OVERSIZE BUSHINGS NOT REQUIRED IAW SB, STANDARD BUSHINGS INSTALLED.  AIRCRAFT TEST FLOWN AND COULD NOT REPRODUCE DEFECT.                                                                                                                                                                                 2L72 4F4  FRTA21EA   E15NE                
20060626001192006062600119EA  2006       6          26         CA060405002      220060405G7200                ENGINE                                                                     PWA   PT6   PT6A50      52043EA                                              MAKING METAL    W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      ENGINE OIL METAL CONTAMINATION WAS REPORTED AND ENGINE SENT TO APPROVED ENGINE FACULITY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               4  T          E4EA                 
20060613001722006061300172WP  2006       6          13         CA060405003      220060316G7261B441172         ADAPTER                                 BEECH 100   B100        1152919CE  GARRTTTPE331TPE3316252B 01514WP  HARTZLHCB4T HCB4TN5     GL  OIL FILTER      CRACKED         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      DURING AN INSPECTION OF THE "OIL FILTER ADAPTER", IT WAS FOUND CRACKED IN TWO PLACES.  A SMALL OIL LEAK WAS EVIDENT.  THE PART WAS REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L72 4T4  T  A14CE   E2WE    6  CP40EA    
20060613001732006061300173EA  2006       6          13         CA060405004      120060331G2730HST22DU522      FASTENER        BOMBDR                  CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30015NE                              ELEVATOR        SHEARED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       22971      RJ7095                                              HI-LIGHT FASTENERS (P/N HST22DU5-22) THAT ATTACHES LINKS (P/N 601R24056-55) TO FITTINGS (P/N 601R24056-51 ON LT AND FITTINGS P/N 601R24056-49 ON THE RT ELEVATOR), FOUND WITH SHEARED HEADS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F4  FRTA21EA   E15NE                
20060613001742006061300174EU  2006       6          13         CA060405005      120060213G2822FRH280002       CANISTER                                AIRBUSA330  A330*              EU  RROYCERB211 RB211*      54555NE                              BOOST PUMP      BROKEN          W      O   OTHER                                                                                           RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  APAPPROACH       1                      CA                                                                      FOB 5100 KG WING CROSSFEED SELECTED ON AS PER ATB 376.  FUEL IS 2500KG IN EACH TANK.  NO FUEL IN OUTERS AND TRIM.  ON SHORT FINAL "L TANK LOW FUEL" ON ECAMLTANK INDICATED 1200 KG AND RIGHT TANK 3500 KG REF SNAG 4205167.  FOUND RT WING NR 1 MAIN BOOST PUMP CANNISTER DELIVERY ELBOW BROKEN AT FLANGE CONNECTION TO FUEL FEED MANIFOLD.  NEW ELBOW INSTALLED WITH NEW SEALS.  OPERATION CHECK OF FEED SYSTEM COMPLETED.  CHECKS SERVICEABLE.                                                                                                                                                                                                                                                                                                2L72 4F4  FRTA46NM   A12EU                
20060613001752006061300175EU  2006       6          13         CA060405006      120060404G33409728787158      LAMP                                    PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  NAV LIGHTS      FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       200        25288300                                            THE A/C WAS MODIFIED PER LSTC 0-LSA06-001/D, INSTALLATION OF LED NAV LAMPS.  LAMPS WERE INTSTALLED PER DRAWINGS ECA-12-TM-05-197.  SINCE THIS INSTALLATION THREE NAV LAMP FAILURES HAVE OCCURRED, ONE TIME ON THE RIGHT LED AND TWICE ON THE TAIL NAV LED.  THE CAUSE IS UNKNOWN AT THIS TIME, HOWEVER PILATUS A/C HAS BEEN NOTIFIED OF THIS PROBLEM.  AT THE FIELD LEVEL, MOISTURE IS SUSPECTED TO BE ENTERING THE UNIT'S THROUGH THE GROMMET WHERE THE WIRING GOES INTO THE LIGHT ASSY.  NO CONCRETE EVIDENCE AT THIS TIME AND WILL WAIT FOR THE MANUFACTURER TO RESPOND ON A FIX FOR THIS PROBLEM.                                                                                                                                           1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20060626001232006062600123NE  2006       6          26         CA060405008      220060119G73143022375         SEAL                                    BEECH 200   B200        1152922CE  PWA   PT6   PT642A           NE  HARTZLHCB3T HCB3TN3     GL  FCU/FUEL PUMP   FAILED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      AIRCRAFT DEPARTED AND ON CLIMB THE PILOT REPORTED A LOW OIL PRESSURE INDICATION ON THE LEFT HAND ENGINE.  THE AIRCRAFT RETURNED TO BASE.  A TECHNICIAN WAS CALLED IN, AND FOUND THAT THE FCU/FUEL PUMP DRIVE SEAL HAD MIGRATED, AND WAS LEAKING.  A NEW SEAL P/N:3022375 AND SEAL CARRIER P/N:3004085 WERE INSTALLED.  ENGINE GROUND RUNS COMPLETED SATISFACTORY, AIRCRAFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                 1L72 4T4  T  A24CE   E4EA    6  CP15EA    
20060613001762006061300176SO  2006       6          13         CA060405009      220060405G8500                ENGINE                                  CESSNA172   172F        2072414CE  CONT  O300  O300C       17022SO  MCAULY1C172 1C172EM     GL                  MAKING METAL    W      K   NONE                                                                                            J  WARNING INDICATION                                                            ININSP/MAINT     1                      CA       2640                                                           OIL SCREEN BYPASS LIGHT CAME ON INFLIGHT.  SCREEN INSPECTION FOUND FERROUS AND NON-FERROUS METAL IN QUANTITY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3O3  ONT3A12    E253    5  NP910     
20060613001772006061300177EA  2006       6          13         CA060405010      120060403G32400860163002      ACCUMULATOR                             CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              BRAKE           MALFUNCTIONED   W      D   RETURN TO BLOCK                                                                                 K  FLUID LOSS                                                                    TXTAXI/GRND HDL  1                      CA       20623                                                          ON TAXI-OUT CREW REPORTED HEARING A LOUD POP AND THE RAMP PERSONNEL NOTIFIED THE CREW OF A HYDRAULIC LEAK FROM THE NOSE AREA AND THE AIRCRAFT RETURNED TO THE GATE. UPON FURTHER INVESTIGATION MAINTENANCE FOUND THE AFT END CAP ON THE BRAKE SYSTEM HYDRAULIC ACCUMULATOR HAD FAILED. WHEN THE END CAP FAILED, IT BLEW THROUGH THE PRESSURE BULKHEAD INTO THE AVIONICS BAY CAUSING DAMAGE TO PITOT AND HYD LINES, BRAKING CONTROL RODS, WIRING AND SURROUNDING STRUCTURE.  ROUTE CAUSE OF THE FAILURE WILL BE PROVIDED ONE THE STRIP REPORT IS AVAILABLE.                                                                                                                                                                                    2L72 4F4  FRTA21EA   E15NE                
20060613001782006061300178EA  2006       6          13         CA060405011      120060331G49901603662         OIL COOLER                              CNDAIRCL600 CL6002B19   1900309EA                                                               APU             LEAKING         W      A   UNSCHED LANDING                                                                                 KB FLUID LOSS                SMOKE/FUMES/ODORS/SPARKS                            CLCLIMB          1                      CA       2819 1528                                                      SHORTLY AFTER TAKEOFF, THE CREW REPORTED SMOKE IN THE CABIN AND RETURNED TO FIELD.  UPON LANDING, THE CREW DISCHARGE THE APU FIRE BOTTLE.  AFTER FURTHER TROUBLESHOOTING, THE SITUATION WAS DUPLICATED AND IT WAS REPORTED THAT THE APU OIL COOLER WAS CLOGGED.  REMOVED AND REPLACED OIL COOLER OPS CHECK GOOD.                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F    RTA21EA                        
20060613001912006061300191EA  2006       6          13         CA060405012      120060326G5610NP13992113      WINDSHIELD                              CNDAIRCL600 CL6002C10   1390015EA                                                               COCKPIT         CRACKED         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA       923                                                            ON CLIMB, THE PILOT WINDSHIELD CRACKED.  A/C RETURNED TO BLOCK.  THIS WAS A POST SB WINDSIELD.  WINDSHIELD WAS REMOVED AND REPLACED IN ACCORDANCE WITH AMM.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F    RTA21EA                        
20060613002812006061300281    2006       6          13         CA060406001      420060329G2311                RELAY                                   CESSNA172   172N        2072434CE  LYC   O320  O320H2AD    41508EA                              UHF SYS         DEFECTIVE       W      A   UNSCHED LANDING                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      APAPPROACH       1                      CA                                                                      RELAY IS USED TO POWER THE RADIO-NAVIGATION SYSTEM.  ON A TRAINING FLIGHT INSTRUMENT APPROACH, SMOKE WAS NOTICED UNDER THE INSTRUMENT PANEL. THE APPROACH WAS ABORTED AND THE AIRCRAFT LANDED WITHOUT INCIDENT.  MAINTENANCE PERSONNEL CARRIED OUT A DETAILED INSPECTION OF ALL THE RADIOS, INSTRUMENTS AND WIRING AND NOTHING WAS DISCOVERED, HOWEVER, WHEN THE 'AVIONICS MASTER' SWITCH WHICH FEEDS THE RADIOS WAS SELECTED 'ON' THE RADIOS BECAME UNSTABLE.  THE AVIONICS MASTER SWITCH WAS SELECTED OFF AND THE AIRCRAFT WAS DISPATCHED TO THE NEAREST AVIONIC FACILITY.                                                                                                                                                                    1H71 3O3  ONT3A12    E274                 
20060626001242006062600124CE  2006       6          26         CA060406002      120060403G5520                TORQUE TUBE                             BEECH 100   B100        1152919CE  GARRTTTPE331TPE3316252B 01514WP  HARTZLHCB4T HCB4TN5     GL  ELEVATOR        CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       12859                                                          DURING AN INSPECTION OF THE ELEVATOR TORQUE TUBE, THE PRIMARY ELEVATOR TORQUE TUBE WAS FOUND CORRODED.  THE PART WAS REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L72 4T4  T  A14CE   E2WE    6  CP40EA    
20060626000062006062600006CE  2006       6          26         CA060406003      120060330G30009755501115      DUCT                                    BEECH 100   A100        1152915CE  PWA   PT6   PT6A28           EA  MCAULY4HFR344HFR34C762  NE  HEAT DUCT       DISCONNECTED    W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      DURING A ROUTINE INSPECTION OF THE CABIN HEATING DUCTS THE HOT AIR DUCT ASSEMBLY P/N 97-555011-15 ITEM NR 22 IN PICTURE NR 1 WAS FOUND DISCONNECTED AT THE AFT END.  2 DUCTS FURTHER FWD WERE FOUND CRACKED ALLOWING THEM TO MOVE FWD AND ALLOWING THIS DUCT TO DISCONNECT FROM ITEM NR 23.   ONCE THE DUCT HAD DISCONNECTED THE CABIN HEAT WAS FLOWING INTO THE FLOOR AND ONTO THE DE-ICE PRESSURE TUBE P/N 50-970101-143 ITEM 81 IN PICTURE NR 2.  THE HEAT ALLOWED A 15 INCH SECTION OF THE DE-ICE TUBE DEFORM AND COLLAPSE RESTRICTING THE AIRFLOW TO THE TAIL PART OF THE DE-ICE SYSTEM. IT IS UNCLEAR WHETHER OR NOT THE TAIL DE-ICE SYSTEM WAS SERVICEABLE.                                                                              1L72 3T4  T  A14CE   E4EA    6  C3PNE     
20061211003722006121100372NM  2006       12         11         CA060406006      120060406G5315                FLOORBEAM                               BOEING737   737290C     138448VNM                                                               BS 1016 S17L    CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) BS 1016 AND STR17L WEB TO FLOOR ATTACH ANGLE CRACKED AND REPAIRED IAW EA AND SRM. (TC NR 20060406006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F      A16WE                        
20061211003742006121100374NM  2006       12         11         CA060406007      120060406G5315                FLOORBEAM                               BOEING737   737290C     138448VNM                                                               BS 807          CORRODED        W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) CORROSION FOUND ON FWD FLANGE OF FLOORBEAM AT BS 807 RBL 56 AND REPAIRED IAW CUSTOMER EA. (TC NR 20060406007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F      A16WE                        
20061211003772006121100377NM  2006       12         11         CA060406008      120060406G5313                STRINGER                                BOEING737   737290C     138448VNM                                                               BS 937 S24L     CORRODED        W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) CORROSION FOUND ON STR 24L AT BS 937 AND REPAIRED IAW CUSTOMER EA (TC NR 20060406008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F      A16WE                        
20060613002822006061300282EA  2006       6          13         CA060406009      120060403G5751C3WA121         ARM                                     DHAV  DHC3  DHC3        2800202EA                                                               AILERON         LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                  FW198                                               MASS BALANCE ARM EXHIBITED LOOSENESS, AND WAS MOVING IN EXCESS OF 1/2 INCH AT THE END WHEN MOVED WITH MINIMAL HAND PRESSURE.  AILERON DISASSEMBLED, FASTENERS REPLACED AND RETURNED TO SAFE AND FIT CONDITION IAW TYPE DESIGN.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H71 3R      A815                         
20060613002832006061300283EA  2006       6          13         CA060407001      120060401G5610NP13932112      WINDSHIELD                              CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              COCKPIT         CRACKED         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA       3089                                                           RT WINDSHIELD CRACKED AT FL180.  FOLLOWED BY "R WSHLD HEAT" MSG.  WINDSHIELD REPLACED IAW AMM 56-11-01.  WINDHIELD WAS A POST SERVICE BULLETIN.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA21EA   E15NE                
20060613002842006061300284EA  2006       6          13         CA060407002      120060330G2710                CONTROL CABLE                           CNDAIRCL600 CL6002C10   1390015EA  GE    CF34  CF348C1          NE                              AILERONS        FROZEN          W      D   RETURN TO BLOCK                                                                                 F  FLT CONT AFFECTED                                                             TXTAXI/GRND HDL  1                      CA       7286                                                           RIGHT AILERON JAMMED IN DOWN POSITION AFTER FLIGHT.  DURING LANDING GROUND ROLL AFTER CROSSWIND LANDING, STUCK CONTROL WHEEL TO RIGHT AFTER RT AILERON INPUT.  RIGHT AILERON IN DOWN-POSITION.  LT AND RT AILERON CABLE CIRCUIT AND PULLEYS CONTAMINATED WITH DEICING FLUID.  CLEANING PERFORMED.  OPERATIONAL TEST OF AILERON CONTROL SYSTEM ACC AMM 27-11-00-710-801-A01, AMM 27-11-00-710-802-A01 PERFORMED.  DOUBLE INSPECTION PERFORMED.                                                                                                                                                                                                                                                                                                   2L72 4F4  FRTA21EA   EOOO63EN             
20061211003792006121100379EA  2006       12         11         CA060407004      120060403G5753                SKIN                                    DHAV  DHC3  DHC3        2800202EA                                                               TE FLAPS        CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) SKIN REPAIRS NOT MADE IAW TYPE DESIGN, AND REPLACED. LEADING EDGE CORRODED, REPAIR MADE IN THE PAST USING INCORRECT (BOGUS) STIFFENER MATERIAL, AND UNPRIMED BY INSTALLER LEAVING A CORRODED MESS.  RETURNED TO CONFORMANCE WITH TYPE DESIGN. (TC NR 20060407004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1H71 3R      A815                         
20060613002862006061300286EA  2006       6          13         CA060407005      120060405G5280CC6701057113    HINGE FITTING                           CNDAIRCL601 CL6012A12   1900303EA  GE    CF34  CF34*            NE                              MLG DOOR        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2279                                                           LHS MAIN LANDING GEAR (MLG) P/N CC670-10520-965, S/N 15042 AND RT MLG DOOR P/N CC670-10520-966, S/N (SAME AS RHS) WERE CRACKED AT THE AFT HINGE FITTING P/N CC670-10571-13 (SEE PIX.1) AND AT FORWARD HINGE FITTING P/N CC670-10570-5 (SEE PIX.2).  LOOSE FASTERNERS WERE ALSO FOUND ON THE INBOARD AND OUTBOARD SIDE OF THE DOORS.                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F4  FRTA21AE   E15NE                
20060613002872006061300287NE  2006       6          13         CA060407006      220060403G7314510767          PUMP                                    AIRTRCAT802 AT802       0390305SW  PWA   PT6   PT6A67A     52043NE                              FUEL SYSTEM     LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       506                                                            DURING DE-INHIBITING INSPECTION, A FUEL LEAK WAS DETECTED AT THE REAR OF THE FUEL PUMP ASSEMBLY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L71 3T4  TNCA19SW   E26NE                
20060613002892006061300289CE  2006       6          13         CA060407007      120060331G77149848025         TACHOMETER                              CESSNA172   172M        2072418CE  LYC   O320  O320E2D     41508EA  MCAULY1C160 1C160DTM    GL  ENGINE          FAILED          W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA            2328                                                      PILOTS FELT ENGINE WAS NOT PRODUCING FULL POWER RETURNED TO BASE.  ENGINE INSPECTED BY AN APPROVED AVIATION COMPANY, ALL ENGINE PARAMETERS WERE NORMAL.  HOWEVER, THEY DISCOVERED THE TACHOMETER WAS 100 RPM LOW AT FULL POWER. REPLACED TACHOMETER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H71 3O3  ONT3A12    E274    5  NP910     
20061211003802006121100380GL  2006       12         11         CA060407008      120060331G5414GS29701378      ACCESS PANEL                            BOMBDRBD700 BD7001A10   1390006GL  RROYCEBR700 BR700710A22009500NE                              FUSELAGE        MISSING         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       1509                                                           (CAN) THE AIRPLANE LANDED AT IT`S DESTINATION WHEN CREW EXITED THE PLANE, THEY NOTICED THAT THE AFT RT BELLY ACCESS PANEL WAS MISSING.  NOTHING WAS NOTICED BY CREW WHILE IN FLIGHT (VIBRATIONS). (TC NR 20060407008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F4  FRTT00003NYE00061EN             
20061213000732006121300073    2006       12         13         CA060410001      420060404G3417ADS86           ADC                                     RAYTHNDH125 HAWKER800XP 7150012CE  GARRTTTFE731TFE7315BR        WP                              COCKPIT         MALFUNCTIONED   W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) THE FLIGHT CREW HAD SNAGGED THE NEUTRAL FUEL TANK FULL INDICATION AS NOT SHOWING FULL WHEN THE TANK WAS ACTUALLY FULL.  IN CONJUNCTION WITH THIS DEFECT THEY ALSO REPORTED THAT THE L/VMO TEST WAS NOT FUNCTIONING.  BOTH THESE DEFECTS WERE ACTIONED AND DURING THE TESTING OF THE L/VMO SYSTEM WE WERE DIRECTED BY THE AMM TO CONDUCT THE ADC SELF TEST IAW MM 34-10-17 ADS-86 TEST.  THE TEST PROCEDURE REQUIRES THAT DURING THE TEST THAT THE (MACH TRIM FAIL) LIGHT ILLUMINATES.  WHEN THE TEST WAS ATTEMPTED, THIS LIGHT DID NOT ILLUMINATE.  BOTH THE AIR CREW MANUAL AND THE MM INDICATED THAT THE LIGHT WILL ILLUMINATE DURING THIS TEST.    THE MACH TRIM SYSTEM WAS FULLY TESTED AND WAS FOUND TO BE FUNCTIONING NORMALLY.  THE2L72 4F4  FRTA3EU    E6WE                 
20061212000732006121200073EU  2006       12         12         CA060410002      120060402G2750532A000004      LIMITER                                 AIRBUS330   A330243     3930330EU  RROYCERB211 RB211*      54555NE                              TE FLAPS        TRIPPED         W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA       1635016350                                                     (CAN) AIRCRAFT ARRIVED WITH THE FLIGHT CONTROL FLAPS FAULT ECAM MESSAGE ON FINAL WHEN SELECTING FLAPS 2IN. UNABLE TO EXTEND FLAPS FROM THE 0 POSITION. DURING TROUBLE SHOOTING, FOUND THE LT FLAP TORQUE LIMITER TRIPPED. TORQUE LIMITER REPLACED AND SYSTEM CHECKED SERVICEABLE.  (TC NR 20060410002)                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA46NM   A12EU                
20060613002922006061300292EU  2006       6          13         CA060410003      120060321G7110F50B258707      DOOR                                    AMD   FALC50FALCON50MYST2730106EU  GARRTTTFE731TFE73131C   01518NE                              S DUCT          DAMAGED         W      C   ABORTED TAKEOFF                                                                                 J  WARNING INDICATION                                                            TOTAKEOFF        1                      CA       7300                                                           DURING TAKEOFF, THE NR 2 ENGINE "FAIL" LIGHT ILLUMINATED.  THE TAKEOFF WAS REJECTED AND THE AIRCRAFT RETURNED TO THE RAMP.  MAINTENANCE WAS CONTACTED AND UPON INVESTIGATION IT WAS DISCOVERED THAT NR 2 ENGINE S DUCT DOOR AFT LATCH HAD NOT BEEN COMPLETELY ENGAGED WITH THE HOOK.  BOTH THE FRONT AND REAR LATCHES WERE RE-ENGAGED AND THE DOOR WAS CHECKED FOR PROPER SECURITY.  THE CREW RESUMED THE FLIGHT AND A NORMAL TAKEOFF WAS CONDUCTED.                                                                                                                                                                                                                                                                                            2L73 4F4  F  A46EU   E6WE                 
20060614000992006061400099NE  2006       6          14         CA060410004      220060409G731402532330003     PUMP                                    BEECH 200   B200        1152922CE  PWA   PT6   PT642A           NE                              RT ENGINE       UNSERVICEABLE   W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         R  PARTIAL RPM/PWR LOSS                                                          CLCLIMB          1                      CA       3946 3946                          PCE94220                    ON TAKEOFF, THE CREWS ROTATED AND HAD RT ENGINE POWER ROLL BACK.  CREWS FEATHERED AND SHUT DOWN THE ENGINE AND TURNED AROUND AND LANDED.  MAINTENANCE FOUND FUEL LEAKING FROM RT ENGINE DRIVEN HIGH PRESSURE FUEL PUMP P/N 025323-300-03.  PUMP ASSY REPLACED AND GROUND RUN, FLIGHT TEST SERVICEABLE.                                                                                                                                                                                                                                                                                                                                                                                                                                          1L72 4T4  T  A24CE   E4EA                 
20061212000742006121200074EU  2006       12         12         CA060410005      120060406G2750                LIMITER                                 AIRBUS330   A330243     3930330EU  RROYCERB211 RB211*      54555NE                              TE FLAPS        MALFUNCTIONED   W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA                                                                      (CAN) AT BEGINNING OF APPROACH, WHEN SELECTING SLATS/FLAPS DOWN, THE FLIGHT CONTROL FLAPS FAULT ECAM CAME ON. UNABLE TO EXTEND FLAPS FROM 0 POSITION. (REPEAT SNAG) DURING INVESTIGATION, FOUND THE LT TORQUE LIMITER AND THE LT ROTARY ACTUATOR TRIPPED. RESET CARRIED OUT. FOUND THE ROTARY ACTUATOR OIL CONTAMINATED WITH WATER.  ALL GEARBOXES AND ROTARY ACTUATORS RE-SERVICED WITH NEW OIL AND FLAPS SYSTEM TESTED SERVICEABLE. CAMPAIGN WAS INITIATED TO REPLACE THE OIL IN ALL GEARBOXES AND ROTARY ACTUATORS OF THE A-330 FLEET.  (TC NR 20060410005)                                                                                                                                                                                  2L72 4F4  FRTA46NM   A12EU                
20060614001012006061400101    2006       6          14         CA060410006      120060406G3213                CYLINDER        MESSIER                                                    PWA   PW120 PW126A           NE  HAMSTD2D    2D30        NE  MLG             CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       23394      DRG721589                                           AT DISASSEMBLY BY FIRST AIR MAINTENANCE SERVICES (EASA APPROVAL NR 145-7030) THE OUTER CYLINDER WAS FOUND TO HAVE SEVERE CORROSION, VIRTUALLY PERFORATED AND ASSESSED AS INELIGIBLE FOR RETURN TO SERVICE.  THE RECORDS INDICATE THE LANDING GEAR ASSEMBLY WAS REMOVED FROM AIRCRAFT SE-LGX (WEST AIR SWEEDEN).                                                                                                                                                                                                                                                                                                                                                                                                                                        4  T          E2ONE   5  CP206     
20061212000772006121200077SW  2006       12         12         CA060410008      120060402G2700212010123101    ROD END                                 BELL  212   212         1181420SW  PWA   PT6T  PT6T3       52045EA                              UNKNOWN         DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       22                                                             (CAN) DURING A SCHEDULED INSPECTION OF THE ROD ENDS, IT WAS NOTED THAT THE BEARING WAS SHOWNING EVIDENCE OF MOVEMENT. BEARING WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20060410008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1G71 4U4  U  H4SW    E22EA                
20060614001032006061400103CE  2006       6          14         CA060410009      120060401G532010541000057     CHANNEL                                 BEECH 76    76          1153005CE  LYC   O360  O360A1G6D        EA                              NLG ACTUATOR    CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      DISCOVERED DURING INSPECTION.  NLG ACTUATOR ATTACH BRACKET WAS FOUND CRACKED FROM THE EDGE OF THE BRACKET, THROUGH A LIGHTENING HOLE AND OUT THE OTHER SIDE.  THE AREA IS DIFFICULT TO INSPECT.  THIS IS THE SUPPORT CHANNEL THAT THE UPPER END OF THE NLG ACTUATOR ATTACHES TO.                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L72 3O3  O  A29CE   E286                 
20060614001052006061400105    2006       6          14         CA060411001      420060404G6122HCB3TN3C        PROPELLER                               EMB   110   EMB110P1    3260122SO  PWA   PT6   PT6A34      52043EA  HARTZLHCB3T HCB3TN3     GL  RIGHT           MALFUNCTIONED   W      C   ABORTED TAKEOFF                                                                                 O  OTHER                                                                         TOTAKEOFF        1                      CA            352                                                       ON THE TAKEOFF ROLL, THE RT PROPELLER RPM WOULD ONLY GO TO 83% AND NOT BEYOND.  THE AIRCRAFT RETURNED TO THE HANGAR WHERE MAINTENANCE FOUND THE RT PROPELLER TO BE AT FAULT.  THE PROPELLER WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE.  THE PROPELLER HAS BEEN SENT TO A REPAIR FACILITY FOR FURTHER INVESTIGATION.                                                                                                                                                                                                                                                                                                                                                                                                                 1L72 4T4  T  A21SO   E4EA    6  CP15EA    
20060614001062006061400106SO  2006       6          14         CA060411002      120060410G3240                BRAKE                                   PIPER PA42  PA42720     7104212SO  PWA   PT6   PT6A61      52043EA                              LEFT            FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         LDLANDING        1                      CA                                                                      LEFT SIDE BRAKE FAILED ON LANDING CAUSING RIGHT MAIN TIRE TO BLOW OUT.  NO DAMAGE TO A/C.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 4T4  T  A23SO   E4EA                 
20061019001962006101900196NM  2006       10         19         CA060412001      120060411G561058935733        WINDOW                                  BOEING737   737522      138449FNM  CFMINTCFM56 CFM563C1    13802EU                              COCKPIT         FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE FLIGHT ON ROUTE THE CAPTAINS NR 4 WINDOW INNER LAYER SHATTERED.AIRCRAFT LANDED AND WINDOW CHANGED.    TIMES- 34660:35   CYCLES- 21649 (TCNR  20060412001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  FRTA16WE   E21EU                
20061212000792006121200079GL  2006       12         12         CA060412002      220060411G73006793969         LINE                                    LKHEED188   188C        5262604SO  ALLSN 501D  501D13      03004GL                              ENGINE          MISSING         W      E   ENGINE SHUTDOWN                                                                                 WY INADEQUATE Q C            ENGINE STOPPAGE                                     NRNOT REPORTED   1                      CA                                                                      (CAN) NR 2 ENGINE HAD A HUNG RESTART WHILE ON A TRAINING FLIGHT, THE ENGINE WAS SHUTDOWN, SECURED AND THE (3) ENGINE PROCEDURES WHEN FOLLOWED ON THE FLIGHT AND LANDING TO THE MAINTENANCE BASE. THE PRIMER PRESSURE LINE WAS FOUND TO BE NOT INSTALLED ON THIS ENGINE. THE PRIMER SYSTEM HAD BEEN PUT BACK INTO SERVICE AFTER THE ENGINE HAD BEEN AQUIRED FROM AN OPERATOR THAT HAD TAKEN THEM OUT OF SERVICE IAW SB. (TC NR 20060412002)                                                                                                                                                                                                                                                                                                      2L74 4T4  T  4A22    E282                 
20061213000882006121300088NM  2006       12         13         CA060412003      120060411G531065225847        BRACKET                                 BOEING727   727227      1384078NM  PWA   JT8   JT8D9A      52048NE                              ENGINE CONTROLS CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) WHILE INVESTIGATING A STIFF THRUST REVERSER SNAG, MAINTENANCE DISCOVERED THE NR 3 ENGINE CONTROL QUADRANT BRACKET CRACKED. BRACKET WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20060412003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L73 4F4  F  A3WE    E2EA                 
20060614001082006061400108NE  2006       6          14         CA060413001      220060406G7250                TURBINE                                 BOEING767   767300      1385204NM  GE    CF6   CF680C2B7        NE                              NR 1 ENGINE     FAILED          W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         EY VIBRATION/BUFFET          ENGINE STOPPAGE                                     CLCLIMB          1                      CA                                          704122                      EGT EXCEEDANCE OF NR 1 ENG DURING CLIMB FOLLOWED BY VIBRATION AND ROLLBACK.  DAMAGE TO LP TURBINE WAS FOUND.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F4  FRTA1NM    E13NE                
20060614001122006061400112SO  2006       6          14         CA060413002      120060406G7603                FRICTION BRAKE                          LKHEED382   382G        526414USO  ALLSN 501D  501D22A     03006GL  HAMSTD54H   54H60117    NE  THROTTLE        DAMAGED         W      E   ENGINE SHUTDOWN                                                                                 F  FLT CONT AFFECTED                                                             DEDESCENT        1                      CA                                                                      DURING TRANSITION TO DESCENT, NR 3 THROTTLE WOULD NOT RETARD FULLY.  THE CREW ELECTED TO CARRY OUT A PRECAUTIONARY SHUTDOWN OF NR 3 ENGINE.  A NORMAL LANDING WAS COMPLETED.  MAINTENANCE WAS UNABLE TO DETECT A FAULT DURING POST FLIGHT ASSESSMENT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2H74 4T4  T  A1SO    E282    6  CP906     
20060614001132006061400113EA  2006       6          14         CA060413003      120060327G3320BR9500106       BALLAST                                 CNDAIRCL600 CL600*             EA  GE    CF34  CF34*            NE                              CABIN LIGHTS    BURNED          W      A   UNSCHED LANDING                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA       2191 2191                                                      EN ROUTE A PASSENGER NOTICED AN ELECTRICAL BURNING SMELL.  HE ALERTED THE F/A WHO ALERTED THE CAPTAIN.  CAPTAIN CONFIRMED THE SMELL.  AIRCRAFT THEN DIVERTED.  AIRCRAFT LANDED UNEVENTFULLY WITH NO NEED FOR EMERGENCY SERVICES.  AIRCRAFT PROCEEDED TO GATE.  IN SPITE OF CREW AND SOC ADVISING STOC THAT THIS WAS A POTENTIAL EMERGENCY, DEPLANEMENT OF PASSENGERS WAS DELAYED 45 MINUTES.  MAINTENANCE FOUND LIGHT BALLAST AT ROW 23 U/S.  BALLAST WAS REMOVED AND NEW BALLAST INSTALLED.  AIRCRAFT WAS VENTED FOR AN EXTENDED PERIOD AND RETURNED TO SERVICE.                                                                                                                                                                               2L72 4F4  FRTA21EA   E15NE                
20060614001212006061400121GL  2006       6          14         CA060413005      220060412G732123070613        FUEL CONTROL                            BELL  206   206L1       1182107SW  ALLSN 250C  250C30P     03013GL                              ENGINE          BROKEN          W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA            1373                                                      ONE OF THE FUEL CONTROL BYPASS COVER SCREWS BROKE CAUSING FUEL TO LEAK INTO THE ENGINE BAY.  THIS IS TO BE INSPECTED EVERY 100 HOURS IAW ALLISON 250 C30 CEB A-73-3075R1 WHICH IT WAS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1G71 3U3  U  H2SW    E1GL                 
20060614001242006061400124SO  2006       6          14         CA060413006      120060413G81204038180047      SEAL            GARRTT                  PIPER PA31  PA31350     7103110SO  LYC   O540  TIO540J2BD  41532EA  HARTZLHCE3Y HCE3YR2A    GL  TURBOCHARGER    FAILED          W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA            1546  YHO36265                                            PRIOR TO A TRAINING FLIGHT THE PILOT NOTED THE LT ENGINE OIL LEVEL TO BE AT 9 QUARTS.  AFTER THE FLIGHT, OIL WAS FOUND ON THE LT GEAR DOOR AND THE ENGINE WAS DOWN TO 6 QUARTS.  MAINTENANCE INSPECTED THE ENGINE AND FOUND OIL AT THE LOW POINT OF THE TURBOCHARGER AND BADLY OIL FOULED SPARK PLUGS.  THE TURBOCHARGER OIL SEAL HAD FAILED AND WAS ALLOWING OIL INTO THE COMPRESSOR SIDE OF THE TURBO.  THE OIL WAS THE BEING INDUCTED INTO THE CYLINDERS WITH A PORTION OF IT BEING BURNED AND A PORTION OF IT BEING EXHAUSTED.                                                                                                                                                                                                              1L72 3O3  O  A20SO   E14EA   5  CP33EA    
20061213000892006121300089NM  2006       12         13         CA060413007      120060413G5313140N01062       STRINGER SPLICE                         BOEING757   757200      1384950NM                                                               BS 1180         CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) CORRODED EXTERNAL STRAP ON RT SIDE OF FUSELAGE AT BS 1180 ALONG STRINGER 17. (TC NR 20060413007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA2NM                         
20061213000902006121300090NM  2006       12         13         CA060413008      120060413G5350148N73081       FAIRING                                 BOEING757   757200      1384950NM                                                               HORIZONTAL STAB CHAFED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) RT HORZ STAB TO BODY SEAL FAIRING LOWER IB GUIDE CHAFED AT FORWARD END. (TC NR 20060413008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F    RTA2NM                         
20061213000912006121300091NM  2006       12         13         CA060413009      120060413G5753                SPAR                                    BOEING757   757200      1384950NM                                                               LT TE FLAP      CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) LT OB MAIN FLAP AFT SPAR UPPER CHORD 44 INCHES OB OF MAIN FLAP IB EDGE. (TC NR 20060413009)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F    RTA2NM                         
20061019001972006101900197NM  2006       10         19         CA060413010      120060413G5754114N40827       SKIN                                    BOEING757   757200      1384950NM                                                               NR 7 SLAT       CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) EXFOLIATED CORROSION AT 2 ADJACENT LOCATIONS (TC NR  20060413010)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F    RTA2NM                         
20060614001752006061400175EA  2006       6          14         CA060414001      320060414G6114                HUB                                     DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO  SNSNCHW69EK W69EK63     EA  PROPELLER       CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1156       AF4209                                              4 INCHES LONGITUDINAL CRACK FROM TIP TO HUB ON NR 2 BLADE.  PROPELLER REMOVED FROM SERVICE.  CRACK SIMILAR TO CRACK ON A/C C-GGMV,                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L71 3O3  ONTTA4CH   E7SO    5  NTA4CH    
20060614002262006061400226EA  2006       6          14         CA060414002      320060414G6111                BLADE                                   DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO  SNSNCHW69EK W69EK63     EA  NR 2            CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1156                                           AF4209          4 INCHES CRACK FROM TIP TO HUB ON NR 2 BLADE, SIMILAR TO THAT REPORTED WITH SDR #20060221008.  PROPELLER REMOVED FROM SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L71 3O3  ONTTA4CH   E7SO    5  NTA4CH    
20060614002282006061400228EA  2006       6          14         CA060417001      220060414G8500                ENGINE                                  BELL  47    47G4        1181030SW  LYC   O540  VO540B1B3   41532EA                                              SHUTDOWN        W      RA  AUTOROTATION            UNSCHED LANDING                                                         YJ ENGINE STOPPAGE           WARNING INDICATION                                  CRCRUISE         1                      CA            286                                                       HELICOPTER WAS FLYING ALONG AND ENGINE QUIT, SUCCESSFUL AUTOROTATION WAS ACCOMPLISHED.  UPON INVESTIGATION OF ENGINE, IT WAS FOUND THAT NONE OF THE VALVES WERE OPENING OR CLOSING AND THEREFORE SUGGESTS THAT CAM SHAFT IS NOT TURNING OR HAS BROKEN, ENGINE IS BEING SENT FOR TEARDOWN INSPECTION AT THIS TIME.                                                                                                                                                                                                                                                                                                                                                                                                                               1G71 3O3  O  2H3     E304                 
20060614002322006061400232CE  2006       6          14         CA060418003      120060407G3297                WIRE                                    BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE  HARTZLHCE4A HCE4A3I     NE  MLG             CHAFED          W      O   OTHER                                                                                           N  FALSE WARNING                                                                 DEDESCENT        1                      CA                                                                      CREW REPORTED LEFT MAIN GEAR NOT INDICATING GREEN BUT WAS DOWN AND LOCKED.  MAINTENANCE FOUND WIRE IN WHEEL WELL AREA CHAFFED TO ACTUATOR DOWNLOCK.  WIRE REPAIRED AND PROTECTED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4T4  TRTA24CE   E26NE   5  CP10NE    
20060614002422006061400242EU  2006       6          14         CA060418004      220060417G7261301350238       COVER                                   BOEING737   737522      138449FNM  CFMINTCFM56 CFM563C1    13802EU                              OIL INLET       SCORED          W      K   NONE                                                                                            K OFLUID LOSS                                          OTHER                     ININSP/MAINT     1                      CA                                                                      MAINTENANCE WAS CARRYING OUT A 7 DAY CHECK ON AIRCRAFT WHEN NOTICED SIGNS OF OIL LEAKING IN THE AFT SECTION OF THE NR 2 ENGINE.  ON INVESTIGATION, THE OIL WAS FOUND TO BE LEAKING PAST THE OIL INLET COVER FOR THE NR 5 BEARING AREA.  THE COVER WAS FOUND TO HAVE SCORING ON THE INTERIOR SMALL RADIUS.  THE COVER WAS REPLACED WITH A SERVICEABLE UNIT.  THIS SAME ITEM WAS REPLACED FOR A SIMILAR PROBLEM IN JULY 2005.                                                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA16WE   E21EU                
20060614002432006061400243EA  2006       6          14         CA060418005      220060414G8520LW13521         MAIN BEARING                            CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              CONNECTING ROD  FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       2154 2154                                                      CONNECTING ROD BEARINGS ON NR 1 AND NR 4 RODS SIGNIFICANT SURFACE DELAMINATION.  BROKEN PIECES 1/2"L BY 1/8"W FOUND IN BETWEEN CONNECTING ROD BEARING AND CRANKSHAFT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1H71 3O3  ONT3A12    1E10                 
20060614002442006061400244EU  2006       6          14         CA060418006      120060413G3260V0214           WARNING HORN                            BRAERO748   HS7482A     4231001EU  RROYCEDART  DART5342         EU  ROTOL R4304 R2124304    EU  MLG             OVERHEATED      W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      CA                                                                      ON TAKEOFF, THE FLIGHT FINE PITCH STOP WARNING HORN SOUNDED FOLLOWED BY AN ACRID SMELL. ON APPROACH THE SHOWING GEAR DOWN AND LOCKED THE CREW OBSERVED AN UNDERCARRIAGE FLAG ON THE ASI AND ELECTED TO HAVE VISUAL CONFIRMATION FROM THE GROUND THAT THE GEAR APPEARED SAFE.  THE AIRCRAFT LANDED AT POINT OF DEPARTURE WITHOUT FURTHER INCIDENT.  MAINTENANCE FOUND THE FFPS HORN SEVERELY OVERHEATED THE HORN WAS REPLACED AND ALL RELATED SYSTEMS WERE CHECKED IN CONJUNCTION WITH NLG SWING.  SMOOTH OVERWEIGHT LANDING CARRIED OUT.  AIRCRAFT RETURNED TO SERVICE.                                                                                                                                                                         2L72 3T4  T  A24EU   A196    6  CP899     
20060614002452006061400245EU  2006       6          14         CA060419001      120060418G3411                PITOT HEAD                              AEROSPATR42 ATR42300    8680920EU  PWA   120   PW120            NE  HAMSTD14SF  14SF5       NE                  OBSTRUCTED      W      C   ABORTED TAKEOFF                                                                                 O  OTHER                                                                         TOTAKEOFF        1                      CA                                                                      DURING TAKEOFF ROLL, THE CREW OBSERVED A 20 KT DIFFERENTIAL BETWEEN ASIS.  THE TAKEOFF WAS REJECTED AND THE AIRCRAFT RETURNED TO RAMP.  MAINTENANCE CLEARED DEBRIS FROM THE CAPT'S PITOT PROBE AND CONDUCTED A SYSTEM LEAK CHECK.  THE AIRCRAFT WAS RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2H72 4T4  TRTA53EU   E20NE   6  CP7NE     
20060614002462006061400246NM  2006       6          14         CA060419002      120060417G5711PA60601         SPAR                                    PIPER PA60  PA60601     7106010NM  LYC   O540  IO540K1J5   41532EA  HARTZLHCC3Y HCC3YR      GL  WING            CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       4634                                                           CRACK WAS NOTICED DURING AN ANNUAL INSPECTION WITH THE AID OF FLASHLIGHT AND MIRROR.  THE DEFECT AREA IS JUST AFT OF THE NR 2 ENGINE FIREWALL THROUGH AN INSPECTION PANEL LOCATED ON THE WING UPPER SURFACE.  MORE INFORMATION TO FOLLOW CONFIRMING THE CRACK(S) WITH HFEC NDT INSPECTION.  ALSO THE WING STATION NUMBER AND PART NUMBER WILL BE PROVIDED.                                                                                                                                                                                                                                                                                                                                                                                      1M72 3O3  ORTA17WE   1E4     5  CP25EA    
20060615001452006061500145EA  2006       6          15         CA060419003      220060407G732243564           SCREW           PRECISION               CESSNA172   172M        2072418CE  LYC   O320  O320E2D     41508EA  MCAULY1C160 1C160CTM    GL  IDLE MIXTURE    LOOSE           W      O   OTHER                                                                                           Y  ENGINE STOPPAGE                                                               APAPPROACH       1                      CA       731        DC45353                                             ON FINAL APPROACH TO LAND, THE ENGINE QUIT.  AIRCRAFT GLIDED TO A LANDING AND ROLLED CLEAR OF THE ACTIVE RUNWAY.  ENGINE WOULD NOT RESTART, PUSHED AIRCRAFT TO PARKING SPOT.  WHEN AME EXAMINED THE ENGINE FOUND THE IDLE MIXTURE CONTROL SCREW HAD WORKED LOOSE AND DEPARTED THE AIRCRAFT IN FLIGHT.  REPLACED MIXTURE SCREW AND ENGINE RAN FINE.  ALL MIXTURE SCREWS WILL BE LOCKWIRED FOR SAFETY FROM NOW ON.                                                                                                                                                                                                                                                                                                                                1H71 3O3  ONT3A12    E274    5  NP910     
20060615001572006061500157CE  2006       6          15         CA060419004      120060407G3260BZ2RQ181A2      LIMIT SWITCH                            BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA  HARTZLHCB3T HCB3T*      GL  MLG             FAILED          W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      CA       16                                                             A NEW LANDING GEAR GEARBOX WAS INSTALLED IN THE AIRCRAFT.  SEVERAL DAYS LATER THE CREW WERE UNABLE TO SELECT THE GEAR UP AFTER TAKEOFF.  THE AIRCRAFT RETURNED AND LANDED NORMALLY.  THE UP LIMIT SWITCH WAS FOUND TO BE DAMAGED WHERE THE INTERNAL CONTACTS WERE NOT MAKING AND NOT ALLOWING THE GEAR TO BE POWERED FOR A GEAR UP SELECTION.  IT IS NOT KNOWN WHEN THE SWITCH WAS DAMAGED AS IT WAS REPLACED AT THE TIME THE GEARBOX WAS REPLACED.  THE SWITCH IS IN AN AREA THAT IS DIFFICULT TO REACH THEREFORE MAKING THE RIGGING ALSO DIFFICULT.                                                                                                                                                                                           1L72 4T4  T  A24CE   E4EA    6  CP15EA    
20060615001582006061500158SO  2006       6          15         CA060419005      220060418G8530                CYLINDER HEAD                           CESSNA182   182N        2072730CE  CONT  O470  O470R       17026SO                              NR 1            LEAKING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       588  588                                                       LEAKAGE FOUND BETWEEN BARREL AND HEAD.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3O3  ONT3A13    E273                 
20060619002422006061900242EU  2006       6          19         CA060419006      120060418G7120332A32323300    TIE BOLT                                SNIAS AS332 AS332L      8680809EU  TMECA MAKILAMAKILA1A    60040EU                              ENGINE MOUNT    SHEARED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) A/C RETURNED FROM AN OFFSHORE TRIP, MAINTENANCE PERSONNEL WERE CARRYING OUT THE TURN AROUND CHECKS AND FOUND THAT ONE OF THE 3 ENGINE TIE BOLTS WAS ONLY HELD IN PLACE BY THE LOCKING WIRE.  ONCE THE LOCK WIRE WAS CUT THE BOLT WAS PULLED OUT AND FOUND TO BE SHEARED IN THE THREADED AREA.  A/C WAS INSPECTED WITH NO OTHER PROBLEMS FOUND, TIE BOLT WAS ORDERED. (TC NR 20060419006)                                                                                                                                                                                                                                                                                                                                                  2G72 4U4  U  H4EU    E12NE                
20060626000082006062600008CE  2006       6          26         CA060419007      120060412G5210504300377       BOLT            BEECH       504300377   BEECH 200   B200        1152922CE  PWA   PT6   PT642A           NE  HARTZLHCD4N3HCD4N3A     GL  PAX DOOR        FAILED          W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA                                                                      WHILE CLIMBING THROUGH 10000 FT, A LOUD BANG WAS HEARD FOLLOWED BY A CONSTANT HISSING SOUND.  THE FLIGHT RETURNED UNEVENTFULLY AND MAINT FOUND THE UPPER FWD DRAW BOLT ROLLER HAD FAILED CAUSING THAT PORTION OF THE DOOR TO SHIFT SLIGHTLY.  BOTH UPPER DRAW BOLT ROLLERS WERE REPLACED AND DOOR INSPECTED FOR FURTHER DAMAGE.  NONE WAS FOUND AND GROUND CHECKS WERE C/O SERVICEABLE.                                                                                                                                                                                                                                                                                                                                                         1L72 4T4  T  A24CE   E4EA    5  CSTC      
20060615001622006061500162GL  2006       6          15         CA060420001      120060410G2820374475          CHECK VALVE                             DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE  HAMSTD2D    2D30        NE  FUEL SYSTEM     CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       5316                                                           ON ROUTINE INSPECTION AFT FUEL CHECK VALVE FOUND CRACKED, P/N 525 GG 1/2D, 3-744-75.  MINOR COLOR TO SHOW THAT FUEL LEAKING.  NO LEAK INDICATION AT LAST INSPECTION 50.20 HOURS PREVIOUS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3R3  RRCA806    5E1     5  CP206     
20060615001652006061500165SW  2006       6          15         CA060420002      120060407G5302206032308003    BULKHEAD                                BELL  206   206L1       1182107SW  ALLSN 250C  250C30      03013GL                              TAILBOOM        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      WHILE PERFORMING 100 HR INSPECTION OF THE ATTACHMENT HOLES FOR TAILBOOM FOUND A CRACK ORIGINATING FROM UPPER RIGHT HOLE.  CRACK WAS 1 INCH IN LENGTH.  BULKHEAD WAS REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1G71 3U3  U  H2SW    E1GL                 
20061213000922006121300092NM  2006       12         13         CA060421001      120060420G5315                FLOORBEAM                               BOEING737   737290C     138448VNM                                                               BS 947          CORRODED        W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) FLOORBEAM CAP AT BS 947 LBL 39 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F      A16WE                        
20061213000932006121300093NM  2006       12         13         CA060421002      120060420G5315                FLOORBEAM                               BOEING737   737290C     138448VNM                                                               BS 967          CORRODED        W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) FLOORBEAM CAP AT BS 967 LBL 18 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F      A16WE                        
20061213000942006121300094NM  2006       12         13         CA060421003      120060420G5713                STRINGER                                BOEING737   737290C     138448VNM                                                               RT WING         CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) RT WING FUEL TANK AT WBL 135.5 STR 2R CRACKED AND REPAIRED IAW EA.  (TC NR 20060421003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F      A16WE                        
20061213000952006121300095NM  2006       12         13         CA060421004      120060420G5313                STRINGER                                BOEING737   737290C     138448VNM                                                               BS 947 S18R     CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) STR 18R AT BS 947 CRACKED AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F      A16WE                        
20070129003132007012900313NM  2007       1          29         CA060421005      120060420G5330                SKIN                                    BOEING737   737290C     138448VNM                                                               FUSELAGE        GOUGED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) BS 867 AT STR 19R SKIN GOUGED AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F      A16WE                        
20070129003142007012900314NM  2007       1          29         CA060421006      120060420G5315                FLOORBEAM                               BOEING737   737290C     138448VNM                                                               FUSEAGE         CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) FLOORBEAM AT BS 767 LBL 24.5 CRACKED AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F      A16WE                        
20070129003152007012900315NM  2007       1          29         CA060421007      120060420G5320                STRUCTURE                               BOEING737   737290C     138448VNM                                                               FUSELAGE        CORRODED        W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) STR 26L BS 380 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F      A16WE                        
20070129003162007012900316NM  2007       1          29         CA060421008      120060420G5534                ATTACH ANGLE                            BOEING737   737290C     138448VNM                                                               VERICAL STAB    CORRODED        W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) VERTICAL STAB LT TRAILING EDGE AT RUDDER STATION 174, PANEL ATTACH ANGLE CORRODED AND REPAIRED IAW CUSTOMER EA (TC NR 20060421008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F      A16WE                        
20061213001002006121300100NM  2006       12         13         CA060421009      120060420G5313                STRINGER                                BOEING737   737290C     138448VNM                                                               BS 520 S26L     CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) STR 26L AT BS 520 CORREDED AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421009)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F      A16WE                        
20061213001012006121300101NM  2006       12         13         CA060421010      120060420G5313                STRINGER                                BOEING737   737290C     138448VNM                                                               BS 500B S16L    CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) STR 16L AT BS 500B+13 INCHES CRACKED AT FASTNER HOLE AND REPAIRED IAW CUSTOMER EA.  (TC NR 20060421010)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F      A16WE                        
20061213001022006121300102NM  2006       12         13         CA060421011      120060420G5313                STRINGER                                BOEING737   737290C     138448VNM                                                               BS 500B-520     CORRODED        W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) STR 26R AT BS 500B TO BS 520 CORRODED AND REPAIRED IAW CUSTOMER EA.  (TC NR  20060421011)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F      A16WE                        
20061213001032006121300103NM  2006       12         13         CA060421012      120060420G5730                SKIN                                    BOEING737   737290C     138448VNM                                                               LWS 76          CHAFED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) LT WING UPPER SKIN, WBL 76.75 FROM AFT EDGE OF SKIN FWD FOR 9.5 INCH SKIN CHAFED AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421012)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F      A16WE                        
20060615001672006061500167EA  2006       6          15         CA060421013      120060417G5610NP1393225       WINDOW                                  CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              COCKPIT         CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA                                                                      THE LEFT COCKPIT WINDOW CRACKED DURING CRUISE AT FL330.  WINDOW REPLACED, AIRCRAFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRTA21EA   E15NE                
20060615001682006061500168NE  2006       6          15         CA060421014      220060416G75324157T43P01      BLEED VALVE                             CNDAIRCL600 CL6002C10   1390015EA  GE    CF34  CF348C1          NE                              4TH STAGE       STICKING        W      A   UNSCHED LANDING                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      CLCLIMB          1                      CA                                                                      AT V1 ON TAKEOFF, SMOKE AFT LAV WARNING ILLUMINATED.  CONTINUED TAKEOFF, DECLARED EMERGENCY AND RETURNED TO ORD.  4TH STAGE SHUTOFF VALVE FOUND DEFECTIVE.  VALVE REPLACED AND OPS CHECK GOOD.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F4  FRTA21EA   EOOO63EN             
20060615001702006061500170CE  2006       6          15         CA060421015      120060402G3397                WIRE                                    LEAR  45    45LEAR      5170805CE  GARRTTTFE731TFE731*     01518WP                              PAX LIGHT       CHAFED          W      H   DEACTIVATE SYST/CIRCUITS                                                                        M  OVER TEMP                                                                     CRCRUISE         1                      CA                                                                      DURING CRUISE, PAX ADVISED CREW PAX TABLE LIGHT SWITCH WAS VERY HOT.  PILOT PULLED CB, OPENED CABIN SIDE PANEL AND DISCONNECTED SWITCH CONNECTORS.  AFTER INVESTIGATION, FOUND LIGHT CONTROL SWITCH P/N: 30600557 (CUSTOMER P/N: SP-45-33) WIRING WAS CHAFING ON CUP HOLDER LOWER BRACKET.  ALSO FOUND CUP HOLDER LATCH WAS MELTED, CUP HOLDER DAMPER (ACTUATOR) SEALS WERE MELTED AND WAS LEAKING, CUP HOLDER SPRING BECAME ANNEALED CONDITION.  NO MORE SPRING ACTION AND THE SIDEWALL AC PLUG PLASTIC COVER WAS DEFORMED DUE TO HEAT.  NOTICE THAT WHEN A SIDEWALL AC PLUG RECEPTACLE WAS INSTALLED, THAT RECEPTACLE WOULD PUSH ON SWITCH WIRING AGAINST CUP HOLDER LOWER BRACKET AND ANY MOVEMENT OF CUP HOLDER WOULD DAMAGE THE WIRING.    2L72 4F4  FRTT00008WIE6WE                 
20060615001752006061500175CE  2006       6          15         CA060421016      120060413G3411AN62704D0300    HOSE                                    LEAR  35    35LEAR      5170600CE  GARRTTTFE731TFE73122B   01518WP                              PITOT STATIC SYSCRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         APAPPROACH       1                      CA                                                                      CREW REPORTED A +- 400FT SPLIT WITH ALTEMETERS.  FOUND PITOT/STATIC HOSE CRACKED.   NOTE: OUR LEARJET 35 FLEET OF AIRCRAFT WERE RVSM CONVERTED WITH A LEARJET STC, THESE HOSES ARE PART OF THE CONVERSION AND FOUND THIS PROBLEM WITH OTHER LEARJET 35 RVSM CONVERTED AIRCRAFTS IN OUR FLEET.                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  F  A10CE   E6WE                 
20060615001772006061500177SO  2006       6          15         CA060421017      120060413G24104111810         ALTERNATOR                              PIPER PA28  PA28R201T   7102813SO  LYC   O360  IO360C1C6   41514EA  MCAULY3D36C B3D36C424   GL  ENGINE          FAILED          W      O   OTHER                                                                                           H  ELECT. POWER LOSS-50 PC                                                       CRCRUISE         1                      CA            220                                                       THE ALTERNATOR HAS BEEN OVERHAULED AND FAILED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L71 3O3  O  2A13    1E10    5  CP58GL    
20060710000232006071000023NM  2006       7          10         CA060421018      120060421G2720591841          DIODE                                   BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                              AILERON/RUDDER  UNKNOWN         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       240                                                            FOUND RUDDER TRIM FAST MOTION RT SIDE WAS U/S.  FAULT CONFIRMED FOUND AILERON/RUDDER TRIM DIODE CR2 WIRE A, UN-CLIP.  PANEL TESTED IAW CMM 27-15-01-700-801.  AFTER FURTHER INVESTIGATION, FOUND CONNECTOR PINS P/N M39029/58-363 INSTALLED WERE WRONG TYPE AND REPLACED WITH PINS P/N M39029/1-101 IN REF TO CMM 27-15-01.  CR2 SPLICE, P/N 591842-1, REPLACED AND TESTED SERVICEABLE IAW CMM 27-15-01, AND SYS TESTED IAW AMM 27-13-16-000-801/-400-801.                                                                                                                                                                                                                                                                                      2H72 4T4  TRTA13NM   E00062EN             
20060619002432006061900243EA  2006       6          19         CA060421019      220060323G852074968           CRANKSHAFT                              BBAVIA8     8GCBC       1220803SW  LYC   O360  O360C2E     41514EA                              ENGINE          CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            847                           L2651636A                   (CAN) FWD INNER DIA CRANKSHAFT CORRODED BEYOND LIMITS IAW AWD 98-02-08. (TC NR 20060421019)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1H71 3O3  O  A21CE   E286                 
20060616000862006061600086EA  2006       6          16         CA060421020      220060323G852074968           CRANKSHAFT                              BBAVIA8     8GCBC       1220803SW  LYC   O360  O360C2E     41514EA                              ENGINE          CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            1500                          L2717736A                   CORROSION FOUND UNDER PID AT FWD ID.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H71 3O3  O  A21CE   E286                 
20060616000872006061600087EA  2006       6          16         CA060421021      220060323G852074968           CRANKSHAFT                              BBAVIA8     8GCBC       1220803SW  LYC   O360  O360C2E     41514EA                              ENGINE          CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            1300                          RL2805636A                  CORROSION FOUND UNDER PID FWD ID.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1H71 3O3  O  A21CE   E286                 
20060803002572006080300257NM  2006       8          3          CA060421022      120060413G3244PNDR0231T       TIRE                                    BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                              MLG             DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       400  53                                                        (CAN) FOUND DURING DAILY CHECK 1 MAIN WHEEL WITH TIRE BEAD WIRE MIGRATION. LOOKS LIKE LOCKING WIRE PROTRUDING FROM TIRE SIDE WALL. WHEEL ASSY HAS BEEN REMOVED. NO TIRE PRESSURE WAS LOST. INVESTIGATION SHOWN THAT THE MIGRATING BEADWIRE HAS DAMAGED THE WHEEL HUB, THE DAMAGED WAS SO DEEP THAT WE HAD TO SCRAP THE AFT WHEEL.  DUNLOP IS AWARE OF THIS MIGRATING BEADWIRE ISSUE CONDITION AND HAS SEEN THIS WIRE COME OUT OF THE TIRE IN THE PAST (SIMILAR TO THIS CONDITION AND IT SEEMS TO BE AN INCREASING PROBLEM).                                                                                                                                                                                                                     2H72 4T4  TRTA13NM   E00062EN             
20061213001042006121300104NM  2006       12         13         CA060421023      120060421G5313                STRINGER                                BOEING737   737290C     138448VNM                                                               BS 350-366      CORRODED        W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) STR 28R, BS 350 TO BS 366 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421023)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F      A16WE                        
20061213001052006121300105NM  2006       12         13         CA060421024      120060421G5313                STRINGER                                BOEING737   737290C     138448VNM                                                               BS 925 S25L     GOUGED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) AFT CARGO PIT STR 25L AT BS 925 HAS A GOUGE AND REPAIRED IAW CUSTOMER EA (TC NR 20060421024)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F      A16WE                        
20061213001062006121300106NM  2006       12         13         CA060421025      120060421G5313                STRINGER                                BOEING737   737290C     138448VNM                                                               BS 947 S26R     GOUGED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) STR 26R AT BS 947 GOUGED AND REPAIRED IAW CUSTOMER EA.  (TC NR 20060421025)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F      A16WE                        
20061213001072006121300107NM  2006       12         13         CA060421026      120060421G5315                FLOORBEAM                               BOEING737   737290C     138448VNM                                                               BS 727B         CORRODED        W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) AFT CARGO PIT FLOORBEAM UPPER CHORD CORRODED AT BS 727B FROM LBL 25-45 AND REPAIRED IAW CUSTOMER EA.  (TC NR 20060421026)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F      A16WE                        
20061213001082006121300108NM  2006       12         13         CA060421027      120060421G5330                SKIN                                    BOEING737   737290C     138448VNM                                                               BS 326 S2R      GOUGED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) FUSELAGE SKIN GOUGED AT BS 326, 2 INCHES ABOVE STR 2R AND REPAIRED IAW CUSTOMER EA.  (TC NR 20060421027)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F      A16WE                        
20061213001092006121300109NM  2006       12         13         CA060421028      120060421G5330                SKIN                                    BOEING737   737290C     138448VNM                                                               BS 500 S25-26L  DENTED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) SKIN HAS SMALL DENT BETWEEN STR 25L AND STR 26L AT BS500+13 AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421028)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F      A16WE                        
20061213001102006121300110NM  2006       12         13         CA060421029      120060421G5322                SHEAR TIE                               BOEING737   737290C     138448VNM                                                               BS 727A S22-23R CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) SHEAR TIE CRACKED AT BS 727A BETWEEN STR 22R AND 23R AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421029)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F      A16WE                        
20061213001152006121300115NM  2006       12         13         CA060421030      120060421G5532                SKIN                                    BOEING737   737290C     138448VNM                                                               VERTICAL STAB   DENTED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) SKIN HAS A DENT IN VERTICAL STAB RT SIDE 12 INCHES AFT OF UPPER END AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421030)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F      A16WE                        
20061213001162006121300116NM  2006       12         13         CA060421031      120060421G5347                SEAT TRACK                              BOEING737   737290C     138448VNM                                                               BS 504-616      CORRODED        W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) CORROSION ON SEAT TRACK BEAM BS 504-616 LBL 26 REPAIRED IAW CUSTOMER EA. (TC NR 20060421031)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F      A16WE                        
20061213001172006121300117NM  2006       12         13         CA060421032      120060421G5315                FLOORBEAM                               BOEING737   737290C     138448VNM                                                               BS 520          CORRODED        W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) FLOORBEAM AT BS 520 LBL 45 CORRODED AND REPAIRED IAW CUSTOMER EA. (TC NR 20060421032)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F      A16WE                        
20061213001182006121300118NM  2006       12         13         CA060421033      120060421G5511                BUSHING                                 BOEING737   737290C     138448VNM                                                               HORIZONTAL STAB CORRODED        W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) RT HORIZONTAL STABILIZER, FRONT AND REAR SPAR BUSHING CORRODED REPAIRED IAW CUSTOMER EA. (TC NR 20060421033)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F      A16WE                        
20061213001192006121300119NM  2006       12         13         CA060421034      120060421G5511                BUSHING                                 BOEING737   737290C     138448VNM                                                               HORIZONTAL STAB CORRODED        W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) LT HORIZONTAL STABILIZER FRONT AND REAR SPAR BUSHINGS CORRODED AND REPAIRED IAW CUSTOMER EA (TC NR 20060421034)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F      A16WE                        
20061213001202006121300120NM  2006       12         13         CA060421035      120060421G5230                SUPPORT ANGLE                           BOEING737   737290C     138448VNM                                                               CARGO DOOR      CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) MAIN CARGO DOOR NR1 LATCH SUPPORTING ANGLE CRACKED REPAIRED IAW CUSTOMER EA. (TC NR 20060421035)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F      A16WE                        
20061213001212006121300121NM  2006       12         13         CA060422000      120060421G5551                ATTACH FITTING                          BOEING737   737290C     138448VNM                                                               HORIZONTAL STAB NICKED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) LT STABILIZER CENTER SECTION AFT UPPER SPAR, UPPER FWD ATTACH LUG FACE NICKED REPAIRED IAW CUSTOMER EA. (TC NR 20060422000)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F      A16WE                        
20061213001222006121300122NM  2006       12         13         CA060422001      120060421G5313                STRINGER                                BOEING737   737290C     138448VNM                                                               BS 947 S26R     GOUGED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) STR 26R AT BS 947 GOUGED REPAIRED IAW CUSTOMER EA. (TC NR 20060422001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F      A16WE                        
20061213001232006121300123NM  2006       12         13         CA060422002      120060421G5510                HINGE FITTING                           BOEING737   737290C     138448VNM                                                               HORIZONTAL STAB GOUGED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) RT HORIZONTAL STAB NR 1 ELEVATOR HINGE FITTING LOWER PORTION HAS A GOUGE REPAIRED IAW CUSTOMER EA. (TC NR 20060422002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F      A16WE                        
20061213001242006121300124NM  2006       12         13         CA060422003      120060421G5315                FLOORBEAM                               BOEING737   737290C     138448VNM                                                               BS 986          CORRODED        W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) FLOORBEAM AT BS 986, LBL 18 TO LBL 52 CORRODED REPAIRED IAW CUSTOMER EA. (TC NR 20060422003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F      A16WE                        
20061213001252006121300125NM  2006       12         13         CA060422004      120060421G5230                STRUCTURE                               BOEING737   737290C     138448VNM                                                               CARGO DOOR      CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) MAIN CARGO DOOR BS492 CRACKED 6 INCHES BELOW HINGE AT FRAME LIGHTNING HOLE TO THE IB EDGE REPAIRED IAW CUSTOMER EA. (TC NR 20060422004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F      A16WE                        
20061213001262006121300126NM  2006       12         13         CA060422005      120060421G5230                SKIN                                    BOEING737   737290C     138448VNM                                                               CARGO DOOR      GOUGED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) MAIN CARGO DOOR SKIN AT NR 6 HINGE ATTACH AREA BS 441.5 GOUGE REPAIRED IAW CUSTOMER EA. (TC NR 20060422005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F      A16WE                        
20061213001272006121300127NM  2006       12         13         CA060422006      120060421G5230                SKIN                                    BOEING737   737290C     138448VNM                                                               CARGO DOOR      GOUGED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) MAIN CARGO DOOR SKIN AT NR 5 HINGE STA 418 GOUGED REPAIRED IAW CUSTOMER EA. (TC NR 20060422006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F      A16WE                        
20061019001982006101900198NM  2006       10         19         CA060422007      120060421G5230                SKIN                                    BOEING737   737290C     138448VNM                                                               CARGO DOOR      GOUGED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) MAIN CARGO DOOR SKIN AT NR 4 HINGE ATTACH AREA STN 492 GOUGED REPAIRED IAW CUSTONER EA (TC NR 20060422007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F      A16WE                        
20061019001992006101900199NM  2006       10         19         CA060422008      120060421G5230                SKIN                                    BOEING737   737290C     138448VNM                                                               CARGO DOOR      GOUGED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) MAIN CARGO DOOR SKIN AT NR 4 HINGE ATTACH AREA STA 406 GOUGED AND REPAIRED IAW CUSTOMER EA (TC NR 20060422008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F      A16WE                        
20060616000882006061600088CE  2006       6          16         CA060422009      120060421G3233130909B40130909 LOCK NUT        BEECH                   BEECH 200   B200        1152922CE  PWA   PT6   PT6A41      52043EA  HARTZLHCB3T HCB3TN3     GL  MLG ACTUATOR    MISSING         W      L   ABORTED APPROACH                                                                                O  OTHER                                                                         APAPPROACH       1                      CA                  F99820                                              DURING L/G EXT IN FLT, LT MAIN AND NOSE GEAR DOWN AND LOCKED IND PRESENT, WITH NO RT IND AND LOUD BANGING SOUND FROM RT SIDE OF A/C.  C/O FLY-BY TO VISUALLY VERIFY ALL THREE LANDING GEARS WERE DOWN.  A/C LANDED SAFELY, VERIFIED ALL 3 L/G WERE DOWN AND LOCKED BEFORE TAXING A/C OFF RUNWAY.  DURING INSPECTION ACT TQ TUBE TO ACT DRIVE BOLT FOUND MISSING.  TQ TUBE END AND ACT DRIVE INSPECTED FOR DAMAGE/CRACKS WITH 10X MAGNIFYING GLASS.  NO DAMAGE EVIDENT.  INNER TQ TUBE SPACER REPLACED DUE TO SOME SCORING OF INNER BORE.  A NEW DRIVE BOLT AND LOCK NUT WAS INSTALLED ON LT AND RT ACT.  LANDING GEAR SYSTEM INSPECTION/RIGGING C/O: GOOD IAW KA200 MM NR 101-590010-19B9 CHAPTER 32-30-00.  FIVE FAULT FREE GEAR SWINGS C/O.   1L72 4T4  T  A24CE   E4EA    6  CP15EA    
20060616000902006061600090EA  2006       6          16         CA060423001      120060330G2710272955          LINK ASSY                               CNDAIRCL600 CL6002C10   1390015EA                                                               AILERONS        BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       4886                                                           RT AILERON OUTBOARD PCU OUTPUT LINK ASSEMBLY BROKEN.  WHILE PERFORMING 5000 HOURS INSPECTION FOR  THE FLUTTER DAMPENER MAINTENANCE FOUND RT AILERON OUTBOARD PCU OUTPUT LINK ASSEMBLY BROKEN.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F    RTA21EA                        
20060616000922006061600092    2006       6          16         CA060424001      220060403G7321414T70P02       FUEL CONTROL                            CNDAIRCL600 CL6002B19   1900309EA                                                               ENGINE          MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 FJ FLT CONT AFFECTED         WARNING INDICATION                                  CLCLIMB          1                      CA       4836                                                           RT ENGINE N1, N2 AND FUEL FLOW FLUCTUATING CLIMBING FROM 10000 FT AND THEN CLIMBING FROM 10000 FT TO FL210 THE RT ENGINE N1, N2 AND FUEL FLOW WERE FLUCTUATING RAPIDLY.  THE FLIGHT DIVERTED AND LANDED WITHOUT INCIDENT.  THE CREW REPORTED THAT FLUCTUATION CEASED WHEN THE THROTTLES WERE RETARDED FOR LANDING.  THE FUEL CONTROL WAS REPLACED IN ACCORDANCE WITH AMM.                                                                                                                                                                                                                                                                                                                                                                       2L72 4F    RTA21EA                        
20060616000972006061600097EA  2006       6          16         CA060424002      120060410G3246AN676AC6300     FLY WIRE                                FOUND FBA   FBA2C       3640102EA  LYC   O540  IO540*      41532EA                              MLG             BROKEN          W      O   OTHER                                                                                           O  OTHER                                                                         APAPPROACH       1                      CA       269                                                            THE AIRCRAFT IS EQUIPPED WITH AEROCET 3450 AMPHIBIAN FLOATS.  AFTER A TWO-HOUR FLIGHT AND AT 3000 FT ALTITUDE ON APPROACH FOR LANDING, THE PILOT HEARD A LOUD NOISE.  NO TURBULENCE WAS NOTED AT THE TIME AND AN UNEVENTFUL LANDING WAS COMPLETED.  UPON GROUND INSPECTION THE FORWARD FLY WIRE (ASSEMBLY P/N: U613) WAS OBSERVED TO HAVE BROKEN APPROXIMATELY 3 1/2 INCHES FROM THE LOWER END.  FLY WIRE WAS REPLACED, AREA INSPECTION CONDUCTED WITH NO FURTHER DISCREPANCIES AND THE AIRCRAFT WAS RETURNED TO SERVICE.  THE PART IN QUESTION HAS BEEN SENT FOR A FAULT ANALYSIS.  A CLOSE VISUAL INSPECTION INDICATED A POSSIBLE FLAW IN THE MATERIAL.                                                                                       1H71 3O3  O  A7EA    1E4                  
20061018000632006101800063EA  2006       10         18         CA060424003      120060424G2620215T950262      FIRE BOTTLE                             CNDAIRCL215 CL2156B11215       EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE                  MALFUNCTIONED   W      F   ACTIVATE FIRE EXT.                                                                              J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      CA       427                                                            (CAN)  1936 :58 CYCLES : 1316 LARGAGES : 8888  ENGLISH: THE INDICATOR FOR NORMAL DISCHARGE OF THE HEATER EXTINGUISHER (YELLOW DISC) DID NOT WORK AND THE BOTTLE DID NOT COMPLETELY EMPTY AFTER DISCHARGE WAS SELECTED.    (TC NR 20060424003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2H72 4T4  TRTA14EA   E20NE   6  CP7NE     
20060616000992006061600099WP  2006       6          16         CA060424004      120060331G7810                CLAMP           ROBSIN                  ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              EXHAUST SHIELD  FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       203        10913                                               DURING PREFLIGHT INSPECTION, TAIL PIPE EXHAUST HEAT SHIELD P/N D317-1 WAS FOUND BENT AFT.  FURTHER INVESTIGATION DETERMINED THAT THE FWD CLAMP FOR THE SHIELD HAD FAILED AND CAME OFF IN FLIGHT ALLOWING THE AIRFLOW TO CATCH THE SHIELD AND BENT IT AFT.  ROBINSON HELICOPTER HAS UPGRADED THE TWO CLAMPS WHICH SECURE THE SHIELD TO A LARGE CLAMP SIZE.  HEAT SHIELD AND CLAMPS REPLACED.                                                                                                                                                                                                                                                                                                                                                     1G71 3O3  O  H11NM   1E4                  
20060616001012006061600101SW  2006       6          16         CA060424005      120060412G531121949           FRAME                                   BBAVIA8     8GCBC       1220803SW  LYC   O360  O360C1E     41514EA  MCAULY1A200 1A200*      GL  FUSELAGE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       7559                                                           DURING THE COMPANY STRUCTURAL INSPECTION AND REPAIR PROGRAM (SIRP), THE RIGHT SIDE OF THE FUSELAGE FRAME WAS FOUND CRACKED IN THE AREA WHERE THE RIGHT MAIN GEAR LEG RESTS AGAINST THE AIRFRAME.  THE CRACK WAS LONGITUDINAL AND WAS ABOUT 1 1/8" LONG.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1H71 3O3  O  A21CE   E286    5  NP874     
20060616001032006061600103SW  2006       6          16         CA060424006      120060424G57535428L           SPAR                                    BBAVIA8     8GCBC       1220803SW  LYC   O360  O360C2E     41514EA  MCAULY1A200 1A200*      GL  LT WING TE FLAP DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      2 HOLES FOR MOUNTING INBD FLAP HINGE BRACKET LWR ATTACH AND INBD BOLT FOR SHIM PLATE BOTH FOUND CRUDELY DRILLED AND VERY OVAL.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H71 3O3  O  A21CE   E286    5  NP874     
20060626000092006062600009NM  2006       6          26         CA060424007      120060422G2612                FIRE LOOP       GARRTT      GTCP85129   BOEING737   737248C     1384415NM  PWA   JT8   JT8D9A      52048NE                              APU             FAULTY          W      F   ACTIVATE FIRE EXT.                                                                              N  FALSE WARNING                                                                 TXTAXI/GRND HDL  1                      CA                                                                      AFTER ARRIVAL AT DESTINATION AND DURING TAXI, A FIRE INDICATION WAS OBSERVED WHEN APU WAS STARTED.  FIRE DRILL CARRIED OUT, EMERGENCY CREW FOUND NO EVIDENCE OF FIRE AND THE AIRCRAFT WAS TOWED TO GATE FOR PASSENGERS DEPLANE.  AIRCRAFT RELEASED ON MEL, APU INOP.                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F4  FRTA16WE   E2EA                 
20060616001052006061600105NM  2006       6          16         CA060424008      120060421G612187620130101     SHAFT                                   DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF15      NE  PROPELLER       BROKEN          W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             NRNOT REPORTED   1                      CA                                                                      FLIGHT CREW REPORTED EXCESS BACKLASH AND PROP SYNC DOES NOT SYNC.  PROP WANDERING + - 5 TO 7 RPM.  ENGINE SPRING STRUT ASSEMBLY REPLACED.  AFTER DISASSEMBLY IN THE O/H SHOP, SHAFT P/N 87620130-101 WAS FOUND BROKEN AT POINT RIVET P/N MS204170AD3. THE SIZE OF THE RIVET HOLE LEAVES MINIMAL MATERIAL AROUND THE SHAFT, WHICH IS PRONE TO BREAKING UNDER VIBRATION.                                                                                                                                                                                                                                                                                                                                                                          2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060616001072006061600107SW  2006       6          16         CA060424009      120060327G6700                YOKE                                    BELL  206   206L3       1182108SW                                                               COCKPIT         OBSTRUCTED      W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      WITH THE COLLECTIVE IN THE MID TO FULL DOWN POSITIONAND THE CYCLIC FULL FORWARDAND LEFT THE RT CONTROL YOKE CONTACTS THE WINDSCREENDEFROST HEATER PIPE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3U      H2SW                         
20060616001292006061600129WP  2006       6          16         CA060425001      120060423G7697VF741H11        RELAY                                   ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              FUEL PUMP       STUCK           W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA       1482                                                           AFTER PRIMING THE ENGINE, IT WAS NOTED THAT THE AUX FUEL PUMP WOULD NOT SHUT OFF.  THE TROUBLE WAS TRACED TO THE CONTROL RELAY.  THE INTERNAL POINTS IN THE RELAY HAD STUCK TOGETHER AND WERE KEEPING THE CIRCUIT CLOSED.  THE RELAY WAS REPLACED, AND NO FURTHER DEFECTS WERE FOUND.                                                                                                                                                                                                                                                                                                                                                                                                                                                           1G71 3O3  O  H11NM   1E4                  
20060616001512006061600151CE  2006       6          16         CA060425002      120060425G571205230821        RIB                                     CESSNA185   A185F       2072821CE  CONT  O520  IO520D      17032SO  MCAULYD3A34 D3A34C403   GL  RT WING         CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       7169                                                           RIGHT WING RIB AT STN 40.125 AFT UPPER FLANGE CRACKED ALONG BEND RADIUS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1H71 3O3  O  3A24    E5CE    5  CP47GL    
20060616001542006061600154NE  2006       6          16         CA060425003      220060402G7200                ENGINE                                  UROCOPEC135 EC135P1     8680990EU  PWA   PW206 PW206B      0    NE                                              DAMAGED         W      O   OTHER                                                                                           XTJENGINE FLAMEOUT           ENGINE CASE PENETRATION   WARNING INDICATION        NRNOT REPORTED   1                      CA                                          BB0084                      DURING FLIGHT, THE ENGINE EMITTED TWO LOUD NOISES ACCOMPANIED BY A CHIP DETECTOR WARNING INDICATION.  TWO MINUTES LATER THE ENGINE FLAMED OUT ON APPROACH.  INSPECTION REVEALED INTERNAL ENGINE DAMAGE, FRACTURE OF AN ENGINE CASE AND RELEASE OF A SEGMENT OF AN ACCESSORY DRIVE GEAR.  PWC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                         1G72 3U3  UO H88EU   E42NE                
20060616001582006061600158NE  2006       6          16         CA060425004      220060405G7261                OIL SYSTEM                              CESSNA560   560XL       2076702CE  PWA   545   PW545A           NE                              ENGINE          LEAKING         W      E   ENGINE SHUTDOWN                                                                                 KB FLUID LOSS                SMOKE/FUMES/ODORS/SPARKS                            CRCRUISE         1                      CA                                          DB0706                      DURING CRUISE, ENGINE OIL PRESSURE WAS SEEN TO FLUCTUATE ACCOMPANIED BY SMOKE AND ODOR IN THE CABIN AIR.  ENGINE OIL PRESSURE SUBSEQUENTLY REDUCED TO ZERO AND THE ENGINE WAS SHUT DOWN IN FLIGHT.  PWC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE, ONCE DETERMINED.                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F4  FRTA22CE   E00059EN             
20060616001592006061600159EA  2006       6          16         CA060425005      220060404G7200                ENGINE                                  DHAV  DHC6  DHC6        2802606EA  PWA   PT6   PT6A27      52043EA                                              POWER LOSS      W      E   ENGINE SHUTDOWN                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      DURING CLIMB, THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION.  THE ENGINE WAS SUBSEQUENTLY SHUT DOWN IN FLIGHT.  P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1H72 3T4  TRTA9EA    E4EA                 
20060616001612006061600161NE  2006       6          16         CA060425006      220060405G7260                TOWERSHAFT                              AEROSPATR42 ATR42*      8680900EU  PWA   PW121 PW121       52124NE                              AGB             DAMAGED         W      O   OTHER                                                                                           XJ ENGINE FLAMEOUT           WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      DURING CRUISE, THE ENGINE EXPERIENCED AN UNCOMMANDED SHUT DOWN.  SUBSEQUENT INSPECTION REVEALED A DISTRESSED ACCESSORY DRIVE TOWER SHAFT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2H72 4T4  TRTA53EU   E20NE                
20060619000522006061900052EA  2006       6          19         CA060425007      220060402G7200                ENGINE                                  PIPER PA46  PA46350P    7104602SO  PWA   PT6   PT6*        52043EA                                              MALFUNCTIONED   W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA                                          RR0052                      DURING CRUISE, ENGINE SPEED INCREASED UNCOMMANDED ACCOMPANIED BY A MANUAL OVERRIDE LIGHT INDICATION.  THE ENGINE WAS SHUT DOWN IN FLIGHT.  FOLLOWING TWO UNSUCCESSFUL ATTEMPTS, THE ENGINE WAS RE-STARTED IN FLIGHT AND THE AIRCRAFT CONTINUED TO DESTINATION.  P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                 1L71 3O3  TRTA25SO   E2NE                 
20060619000542006061900054NE  2006       6          19         CA060425008      220060410G7200                ENGINE                                  MRCHTIS205  S20522R     8120412EU  PWA   JT15  JT15*       52060NE                                              MALFUNCTIONED   W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      CA                                          98023                       DURING TAXI, THE ENGINE WAS FOUND NOT TO RESPOND TO THROTTLE INPUT AND SUBSEQUENTLY EXPERIENCED AN UNCOMMANDED POWER REDUCTION.  THE ENGINE WAS SHUT DOWN.  P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L71 3O4  T  A9EU    E1NE                 
20060619000592006061900059EA  2006       6          19         CA060425009      220060409G7200                ENGINE                                  BEECH 90    C90A        1152911CE  PWA   PT6   PT6A21      52043EA                                              MALFUNCTIONED   W      E   ENGINE SHUTDOWN                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  APAPPROACH       1                      CA                                          PE0126                      ON APPROACH, ENGINE TORQUE AND FUEL FLOW WERE SEEN TO FLUCTUATE.  THE ENGINE WAS SUBSEQUENTLY SHUT DOWN IN FLIGHT.  P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L72 3T4  TRT3A20    E4EA                 
20060619000622006061900062NE  2006       6          19         CA060425010      220060408G7200                ENGINE                                  BRAERO1000  BAE1251000  1500287EU  PWA   305   PW305B      52128NE                                              MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 RXJPARTIAL RPM/PWR LOSS      ENGINE FLAMEOUT           WARNING INDICATION        CRCRUISE         1                      CA                                          305031                      DURING CRUISE, THE ENGINE SURGED FOLLOWED BY AN UNCOMMANDED POWER REDUCTION TO IDLE.  THE WAS NO SUBSEQUENT RESPONSE TO THROTTLE INPUT.  P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F4  FRTA3EU    E35NE                
20060619000652006061900065NE  2006       6          19         CA060425011      220060407G7250                TURBINE BLADES                          BEECH 45    T34C1       1152016CE  PWA   PT6   PT6A25      52043NE                              ENGINE          DAMAGED         W      A   UNSCHED LANDING                                                                                 BRXSMOKE/FUMES/ODORS/SPARKS  PARTIAL RPM/PWR LOSS      ENGINE FLAMEOUT           NRNOT REPORTED   1                      CA                                          48053                       DURING A TRAINING FLIGHT, THE ENGINE WAS REPORTED TO EMIT NOISES AND SMOKE FOLLOWED BY AN UNCOMMANDED POWER REDUCTION AND FLAME OUT.  SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES.  P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L71 3T3  T  A26CE   E4EA                 
20060619002582006061900258NE  2006       6          19         CA060425012      220060416G7261                ENGINE                                  AEROSPATR72 ATR72              EU  PWA   PW120 PW127            NE                              OIL SYS         LEAKING         W      A   UNSCHED LANDING                                                                                 KRJFLUID LOSS                PARTIAL RPM/PWR LOSS      WARNING INDICATION        CLCLIMB          1                      CA                                                                      DURING CLIMB, ENGINE LOW OIL PRESSURE WARNING ACTIVATED.  ENGINE SUBSEQUENTLY EMITTED A NOISE AND EXPERIENCED AN UNCOMMANDED POWER REDUCTION.  POST-FLIGHT INSPECTION REVEALED NO OIL REMAINING IN THE ENGINE AND SEIZURE OF THE HIGH PRESSURE ROTOR.  MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED.                                                                                                                                                                                                                                                                                                                                                                                                            2H72 4T4  TRT        E20NE                
20060619002602006061900260NM  2006       6          19         CA060425013      120060425G2913623337          PUMP                                    BOEING737   737522      138449FNM  CFMINTCFM56 CFM563C1    13802EU                              HYD SYSTEM      FAILED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      AFTER TAKEOFF, CREW NOTICED A LOW HYDRAULIC PRESSURE INDICATION WHEN THE LANDING GEAR WAS RETRACTED.  LATER IN THE CLIMB THERE WAS AN INDICATION FOR LOSS OF HYDRAULIC PRESSURE FROM THE NR 1 ENGINE DRIVEN PUMP.  THE CREW ELECTED TO RETURN TO BASE FOR MAINTENANCE DUE TO THE UNAVAILABILITY OF REPLACEMENT PARTS AT THEIR DESTINATION.  THE AIRCRAFT RETURNED AND LANDED WITHOUT INCIDENT.  MAINTENANCE REPLACED THE NR 1 ENGINE DRIVEN HYDRAULIC PUMP.  AFTER SUCCESSFUL LEAK AND PRESSURE CHECKS, THE AIRCRAFT WAS RETURNED TO SERVICE.                                                                                                                                                                                                   2L72 4F4  FRTA16WE   E21EU                
20060619001452006061900145NE  2006       6          19         CA060425014      220060416G7200                ENGINE                                  CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE                                              FLAMED OUT      W      A   UNSCHED LANDING                                                                                 XJ ENGINE FLAMEOUT           WARNING INDICATION                                  CLCLIMB          1                      CA                                          PC0880                      DURING CLIMB, THE ENGINE EMITTED A LOUD NOISE AND FLAMED OUT.  A DEADSTICK LANDING WAS SUCCESSFULLY ACCOMPLISHED.  P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H71 3T3  T  A37CE   E4EA                 
20060619001462006061900146NE  2006       6          19         CA060425015      220060405G7240                TURBINE BLADES                          AYRES S2    S2RT34NORMAL0970106SO  PWA   PT6   PT6A34AG    52053NE                              ENGINE          FRACTURED       W      A   UNSCHED LANDING                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      CLCLIMB          1                      CA                                                                      ON TAKEOFF, THE ENGINE WAS SEEN TO EMIT SMOKE AND SPARKS FROM THE EXHAUST.  SUBSEQUENT INVESTIGATION REVEALED FRACTURED COMPRESSOR TURBINE BLADES.  PWC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L71 3T4  T  A3SW    E4EA                 
20060619001472006061900147NE  2006       6          19         CA060425016      220060417G7230                COMPRESSOR                              CESSNA500   560CESSNA   2076750CE  PWA   JT15  JT15D5      52112NE                              ENGINE          STALLED         W      A   UNSCHED LANDING                                                                                 BRJSMOKE/FUMES/ODORS/SPARKS  PARTIAL RPM/PWR LOSS      WARNING INDICATION        CLCLIMB          1                      CA                                          500037                      DURING CLIMB, THE ENGINE EXPERIENCED COMPRESSOR STALLS ACCOMPANIED BY AN UNCOMMANDED POWER ROLL-BACK AND FUMES IN THE CABIN AIR.  THE FLIGHT WAS DIVERTED.  SUBSEQUENT INSPECTION REVEALED LP COMPRESSOR BOOST ROTOR DAMAGE.  P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED.                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F4  FRTA22CE   E25EA                
20060619002692006061900269NE  2006       6          19         CA060425017      220060420G7200                ENGINE                                  AEROSPATR72 ATR72212    8680945EU  PWA   PW120 PW127            NE                                              MALFUNCTIONED   W      EC  ENGINE SHUTDOWN         ABORTED TAKEOFF                                                         RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  TOTAKEOFF        1                      CA                                                                      ON TAKEOFF AND CLIMB, THE ENGINE WAS REPORTED TO EXHIBIT PARTIAL POWER LOSS AND WAS SHUTDOWN IN FLIGHT.  POST-FLIGHT INSPECTION REVEALED NO ANOMALIES.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2H72 4T4  TRTA53EU   E20NE                
20060619002752006061900275NE  2006       6          19         CA060425018      220060424G7200                ENGINE                                  DHAV  DHC8  DHC8*              NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF23      NE  NR 1            MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      ON TAKEOFF, THE NR 1 ENGINE AUTOFEATHERED AND THE NR 2 ENGINE UP TRIMMED.  THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060619002762006061900276CE  2006       6          19         CA060425019      120060425G5414999800007       SKIN                                    BEECH 99    99          1154002CE  PWA   PT6   PT6A27      52043EA  HARTZLHCB3T HCB3TN3     GL  LT NACELLE      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       33536                                                          VISUAL INSPECTION INDICATED A CRACK ON LT ENGINE NACELLE IB SKIN JUST FORWARD OF WING LEADING EDGE.  CRACK RAN VERTICALLY JUST AFT OF IB NACELLE INSPECTION PANEL.  A RIVET THAT ATTACHES THE NACELLE FILLET STRIP TO THE WING WAS INCLUDED IN THE CRACK.  THERE WAS NO REPORT OF A HARD LANDING AND NO ADJACENT STRUCTURE IS DAMAGED.                                                                                                                                                                                                                                                                                                                                                                                                          1L72 3T4  T  A14CE   E4EA    6  CP15EA    
20060619002772006061900277NE  2006       6          19         CA060425020      220060422G7320                HMU                                     CESSNA500   550         2076604CE  PWA   530   PW530A           NE                              ENGINE          MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 RFJPARTIAL RPM/PWR LOSS      FLT CONT AFFECTED         WARNING INDICATION        CRCRUISE         1                      CA                                                                      ON TAKEOFF ROLL, ENGINE POWER ROLLED BACK MARGINALLY AND WAS CORRECTED BY A THROTTLE ADJUSTMENT.  POWER FLUCTUATIONS WERE REPORTED DURING CLIMB.  IN CRUISE, POWER ROLLED BACK UNCOMMANDED AND THE ENGINE WAS FOUND NOT TO RESPOND TO THROTTLE INPUT.  THE AIRCRAFT DIVERTED AND ON DESCENT ENGINE THROTTLE AUTHORITY WAS REGAINED.  MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                             1L72 4F4  F  A22CE   E00053EN             
20060807000522006080700052CE  2006       8          7          CA060426001      120060405G71207120000101      MOUNT                                   SYMPHOSA160 SA160       05619SUCE  LYC   O320  O320D2A     41508EA                              ENGINE          DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) INSPECTION FOR ISSUANCE OF A C OF A AIRCRAFT TOTAL TIME: 2.8 HRS DURING THE INSPECITON OF THIS AIRCRAFT BY CIVIL AVIATION INSPECTOR, IT WAS NOTED THAT AN ENGINE CONTROL SUPPORT BRACKET WAS CONTACTING THE LOWER TUBE OF THE ENGINE MOUNT.  NO DAMAGE TO THE ENGINE MOUNT WAS NOTICED BUT THE PAINT FINISH WAS MARKED BY CHAFFING.  ACTION TAKEN; ENGINE MOUNT BRACKET 760-02043-01 WAS SLIGHTLY RELOCATED ON 760-02041-01 CONTROL SUPPORT BRACKET TO ADD CLEARANCE FOR ENGINE VIBRATIONS AND MOVEMENTS. (TC# 20060426001)                                                                                                                                                                                                               1H71 3O3  ONTA46CE   E274                 
20060621000892006062100089GL  2006       6          21         CA060426003      220060424G7200                ENGINE                                  CVAC  340   340CVAC     242270AWP  ALLSN 501D  501D22      03005GL  HAMSTD54H   54H60       NE                  FAILED          W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CRCRUISE         1                      CA            5056                          501636                      (CAN) DURING CRUISE, THE CREW NOTICED THE TIT SPIKED TO 1100 DEGRESS F. THE HORSEPOWER DECREASED AND THE ZONE 1 FIRE BELL SOUNDED. THE E HANDLE AWAS PULLED AND THE ENGINE WAS SHUT DOWN AND THE PROPELLER FEATHERED. THE AIRCRAFT LANDED. MAINTENANCE CREW INSPECTED THE AIRCRAFT AND NO STRUCTURAL DAMAGE WAS NOTED. THE ENGINE QEC WILL BE REPLACED WITH A SERVICEABLE UNIT. THE ENGINE IS BEING RETURNED AND WILL BE INSPECTED TO DETERMINE THE CAUSE OF THE FAILURE. (TC NR 20060426003)                                                                                                                                                                                                                                                   2L72 4R4  T  6A6     E282    6  CP906     
20060621001162006062100116CE  2006       6          21         CA060427000      120060403G712050980002185     MOUNT                                   BEECH 200   200BEECH    1152920CE  PWA   PT6   PT642A           NE  HARTZLHCB3T HCB3TN3     GL  ENGINE          LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) BOTH LOWER ENGINE MOUNT FITTINGS P/N 50-980002-185 CONTAINING THE ENGINE MOUNT BARREL NUTS WERE FOUND LOOSE BY LIFTING ON THE NON ENGINE MOUNT AND OBSERVING THE LOWER LEGS OF THE MOUNT IN RELATION TO THE FIREWALL. THE OB FITTING HAD MORE MOVEMENT THAN THE IB.  AN ENGINE MOUNT WOULD TAKE A HARDER LIFT TO SHOW MOVEMENT. THE FASTENERS ARE VISIBLE THROUGH THE NACELLE SIDE HATCHES. IF LOOSE THEY COULD EXHIBIT HEAVY SMOKING AND A BLACK GREASE LIKE BUILDUP AT EACH FASTENER. (TC NR 20060427000)                                                                                                                                                                                                                               1L72 4T4  T  A24CE   E4EA    6  CP15EA    
20060621001172006062100117EA  2006       6          21         CA060427001      220060419G852013S19646        GEAR                                    CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              CRANKSHAFT      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2154 2154                          L2866351A                   (CAN) CRANKSHAFT GEAR HAD TWO SMALL MPI INDICATIONS ON ONE GEAR TOOTH. THE GEAR ALSO HAD VISUAL DAMAGE TO 3 GEAR TEETH. CRANKSHAFT GEAR WAS REMOVED FROM SERVICE AND REPLACED WITH NEW GEAR. (TC NR 20060427001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1H71 3O3  ONT3A12    1E10                 
20060621001182006062100118EA  2006       6          21         CA060427002      220060413G852074502           CONNECTING ROD                          PIPER PA25  PA25235     7102504SO  LYC   O540  O540B2B5    41532EA                              ENGINE          GALLED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            192                           L893440                     (CAN) CONNECTING RODS REMOVED FROM ENGINE AT 192.0HRS DUE TO PROP STRIKE. RODS INSPECTED IAW SB439A, AND ALL 6 RODS HAD FRETTING AND GALLING ON THE CONNECTING ROD BEARING BORE SURFACE. THE RODS WERE REPAIRED AND RETURNED TO SERVICE. THE PREVIOUS OVERHAUL RECORDS HAD NOT INDICATED COMPLIANCE WITH SB439A. (TC NR 20060427002)                                                                                                                                                                                                                                                                                                                                                                                                            1L71 3O3  O  2A10    E295                 
20060621001202006062100120SW  2006       6          21         CA060427003      120060419G291027810061011     LINE                                    SWRNGNSA227 SA227*             SW  GARRTTTPE331TPE33111U   01514WP  MCAULY4HFR344HFR34C652  NE  HYDRAULIC SYS   LEAKING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) AIRCRAFT WAS SITTING IN THE HANGER WHEN MAINTENANCE NOTICED A PUDDLE OF HYD FLUID ON THE GROUND UNDER THE AIRCRAFT BY THE LT CENTER SECTION, STATION 27.103.  THE LINE HAD A HAIRLINE CRACK AT THE FWD BEND INSIDE THE WING CENTER SECTION.  THE LINE WAS PART OF THE GEAR UP PRESSURE SYSTEM.  THE LINE WAS REPLACED AND GEAR SWINGS CARRIED OUT SERVICIBLE. (TC NR 20060427003)                                                                                                                                                                                                                                                                                                                                                         2L72 4T4  TRTA5SW    E4WE    6  C3PNE     
20060621001222006062100122NM  2006       6          21         CA060427004      120060425G2130                SHUTOFF VALVE                           BOEING727   727233      138408ANM  PWA   JT8   JT8D15      52051NE                              CABIN PRESSURE  MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) CLIMBING THROUGH FL20 THE F/E ADVISED OF PRESSURIZATION PROBLEMS. AFTER REDUCING TO 10,000 FT. CABIN INDICATED 10,000 WITH 3 PSI DIFF.WHEN THRUST REDUCED THE DIFF WAS 0. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE. MAINTENANCE REPLACED THE PRESSURIZATION CONTROL PANEL AND THE PRESSURE CONTROL MODULATING SOV. THE SYSTEM WAS FUNCTION CHECKED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 020060427004)                                                                                                                                                                                                                                                                                                                          2L73 4F4  FRTA3WE    E2EA                 
20060621001242006062100124    2006       6          21         CA060427005      420060425G3497688160          WIRE                                    PIPER PA42  PA42720     7104212SO  PWA   PT6   PT6A61      52043EA  HARTZLHCB3T HCB3TN3     GL  SWITCH          CORRODED        W      HA  DEACTIVATE SYST/CIRCUITSUNSCHED LANDING                                                         B  SMOKE/FUMES/ODORS/SPARKS                                                      CLCLIMB          1                      CA       9201                                                           (CAN) DURING CLIMB FLIGHT CREW SMELLED AND VISUALLY CONFIRMED SMOKE IN COCKPIT. THEY SHUTOFF WINDSHIELD HEAT AND PITOT/STALL HEAT AND SMOKE DISSIPATED. FLIGHT RETURNED TO POINT OF DEPARTURE FOR INVESTIGATION. MAINTENANCE FOUND SURFACE CORROSION ON PITOT/STALL HEAT SWITCH WIRING CONNECTORS. CONNECTORS AND SWITCH REPLACED NEW. OPERATIONS CHECK C/O SATISFACTORY AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20060427005)                                                                                                                                                                                                                                                                                                                  1L72 4T4  T  A23SO   E4EA    6  CP15EA    
20060621001272006062100127EA  2006       6          21         CA060427007      120060425G2910AN62498         CHECK VALVE                             CNDAIRCL215 CL2151A10   1900320EA  PWA   R1340 CWASP       52016NE  HAMSTD43E   43E60       NE  HYD SYSTEM      SEPARATED       W      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CLCLIMB          1                      CA       4050 4050                                                      (CAN) AFTER COMPLETING A WATERDROP, BOTH WATERDOORS FAILED TO CLOSE AND LOCK. AC EXPERIENCED A COMPLETE HYDR FAILURE CAUSED BY FAILURE OF ONE-WAY CHECK VALVE IN MAIN PRESSURE LINE AT WING STA 54 ON RT WING LE. THIS CHECK VALVE'S PURPOSE IS TO STOP HYD PRESSURE FLOWING BACK TO ENG DRIVEN PUMP WHEN USING GROUND TEST EQUIPMENT, AUXILARY HYD PUMP.  AC PERFORMED EMERGENCY LANDING GEAR EXTENSION, RETURNED TO BASE, LANDED SAFELY.  CHECK VALVE HSG IS CONSTRUCTED OF ALUMINUM. AFTER RECEIVING REPORTS OF FAILURE OF THIS CHECK VALVE, MFG PRODUCED SB 215-0466(STAINLESS STEEL CHECK VALVES)TO RECTIFY THIS PROBLEM. OUR ORGANIZATION WILL EMBODY THIS SB.  ORDERED THESE CHECK VALVES(2 PER AC) TO BE INSTALLED. (TC NR 20060427007) 2H72 4R3  RRTA14EA   ATC14   6  CP871     
20060621001282006062100128WP  2006       6          21         CA060428001      220060427G7261P1070           OIL FILTER                              SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP  HARTZLHCE4N HCE4N3      NE  ENGINE          BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       45                                                             (CAN) DURING A ROUTINE DAILY INSPECTION THE OIL FILTER BYPASS PIN WAS FOUND POPPED INDICATING AN OBSTRUCTED OIL FILTER. UPON INSPECTION OF THE FILTER IT WAS FOUND TO BE BROKEN AT THE OIL INLET MOUNTING FLANGE. PREVIOUS SDR'S HAVE BEEN ISSUED FOR THIS PROBLEM, REFERENCE SDR NR 20031024003, 20031024002, 20031024004. A OIL SAMPLE WAS COMPLETED ON THE ENGINE.  THE FILTER WHICH WAS REMOVED WAS A PMA FILTER WITH A PART NUMBER OF P-1070.  OEM FILTER NORMALLY USED IS A 3001436-1. (TC NR 20060428001)                                                                                                                                                                                                                                2L72 4T4  TRTA8SW    E4WE    5  CP10NE    
20060621001302006062100130    2006       6          21         CA060428002      420060428G3421175E28CT        TRANSFORMER                             CNDAIRCL601 CL6012A12   1900303EA  GE    CF34  CF343A      30015NE                              INDICATOR       INOPERATIVE     W      A   UNSCHED LANDING                                                                                 H  ELECT. POWER LOSS-50 PC                                                       CRCRUISE         1                      CA                                                                      (CAN) LOSS OF NR 1 MASI, NR 1 ALTIMETER, FDR, NR 1 ADI PITCH AND ROLL INFO, COMPASS INFO, NR 1 ESSENTIAL BUS AND LOSS 26 VAC. CAUSE OF FAULT FOUND TO BE BROKEN WIRES AT T2XD POST NR 3.  TRANSFORMER LOCATED ON BACK OF C/B PANEL C. (TC NR 20060428002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F4  FRTA21AE   E15NE                
20060621001312006062100131SO  2006       6          21         CA060428003      120060425G2912460635          FILTER                                  PIPER PA31  PA31350     7103110SO  LYC   O540  TIO540J2BD  41532EA  HARTZLHCE3Y HCE3YR2A    GL  HYD SYSTEM      CRACKED         W      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  DEDESCENT        1                      CA                                                                      (CAN) ON LANDING THE AIRCRAFT LOST HYD PRESSURE AND A EMERGENCY EXTENTION WAS SUCCESSFULLY CARRIED OUT.  ON INSPECTING THE CAUSE OF THE HYD LEAK THE RT FILTER BOWL WAS FOUND TO BE LEAKING. WHEN REMOVING THE BOWL THE THIRD THREAD DOWN FROM THE TOP OF THE BOWL WAS FOUND CRACKED (ABOUT HALF WAY AROUND THE BOWL) ALLOWING THE FILTER BOWL TO TIP TO A ANGLE ALLOWING THE HYD PRESSURE TO BLOW THE FLUID OUT.  A NEW ASSY WAS INSTALLED WITH NO MORE PROBLEMS REPORTED. (TC NR 20060428003)                                                                                                                                                                                                                                                 1L72 3O3  O  A20SO   E14EA   5  CP33EA    
20060623000412006062300041NE  2006       6          23         CA060501001      220060426G7200                ENGINE                                  CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE                                              FAILED          W      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA                                          19265                       (CAN) DURING CRUISE THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY AN UNCOMMANDED POWER LOSS.  THE ENGINE WOULD NOT RESPOND TO THROTTLE INPUT.  A SUCCESSFUL DEAD-STICK LANDING WAS ACCOMPLISHED.   MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060501001)                                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3T3  T  A37CE   E4EA                 
20060623001532006062300153EA  2006       6          23         CA060501002      220060426G7200                ENGINE                                  BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                                              FLAMED OUT      W      C   ABORTED TAKEOFF                                                                                 XJ ENGINE FLAMEOUT           WARNING INDICATION                                  TOTAKEOFF        1                      CA                                          FA0130                      (CAN) ON TAKEOFF ROTATION THE ENGINE EMITTED A LOUD NOISE AND FLAMED OUT.  TAKEOFF WAS ABORTED.  MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060501002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2H72 4T4  TRTA13NM   E00062EN             
20060623001542006062300154EA  2006       6          23         CA060501003      220060407G7321324475520       FUEL CONTROL                            BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA                              ENGINE          FAILED          W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         R  PARTIAL RPM/PWR LOSS                                                          CRCRUISE         1                      CA            1650                                                      (CAN) DURING CRUISE THE ENGINE EXPERIENCED AN UNCOMMANDED POWER ROLL-BACK.  THE ENGINE WAS SHUTDOWN IN FLIGHT.  THE FUEL CONTROL UNIT WAS SUBSEQUENTLY REPLACED. (TC NR 20060501003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L72 4T4  T  A24CE   E4EA                 
20060623001552006062300155SW  2006       6          23         CA060501004      120060428G56103600151         WINDOW                                  GULSTM690TP 690D        3970405SW  GARRTTTPE331TPE3315     01514WP  ROTOL R306  R306382F7   GL  COCKPIT         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) COCKPIT LT OVERHEAD WINDOW SHOWED SIGNS OF PRESSURIZATION LEAK.  WINDOW REMOVED TO REPLACE GASKET AND FOUND WINDOW CRACKED.  CRACKS ORIGINATING FROM 4 SCREW ATTACHMENT HOLES.  NEW WINDOW INSTALLED. (TC NR 20060501004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1H72 3T4  T  2A4     E4WE    6  CP8EU     
20060623001562006062300156SW  2006       6          23         CA060501005      120060428G56103600152         WINDOW                                  GULSTM690TP 690D        3970405SW  GARRTTTPE331TPE3315     01514WP  ROTOL R306  R306382F7   GL  COCKPIT         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) COCKPIT RT OVERHEAD WINDOW REMOVED FOR INSPECTION AFTER FINDING THE LT WINDOW CRACKED.  WINDOW FOUND TO HAVE 2 CRACKS ORIGINATING FROM 2 SCREW ATTACHMENT HOLES. WINDOW REPLACED WITH NEW. (TC NR 20060501005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H72 3T4  T  2A4     E4WE    6  CP8EU     
20060623001582006062300158CE  2006       6          23         CA060501006      120060417G71601019100203      VANE                                    BEECH 200   200BEECH    1152920CE  PWA   PT6   PT642A           NE  MCAULY3AF34C3GFR34C703  GL  INTAKE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) VANE FOUND SEVERELY CRACKED ON VISUAL INSPECTION. CRACK APPEARS TO HAVE STARTED AT LEADING EDGE OF VANE FROM THE HINGE AREA. HINGE WAS FOUND CRACKED ALSO.  DAMAGE POSSIBLY ACCELERATED DUE TO FLUTTER OF THE DAMAGED VANE. (TC NR 20060501006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L72 4T4  T  A24CE   E4EA    5  CP60GL    
20060623001592006062300159CE  2006       6          23         CA060502000      120060424G57305012016318      SKIN                                    BEECH 100   100BEECH    1152916CE  PWA   PT6   PT6A28           EA  HARTZLHCD4N3HCD4N3A     GL  WING            CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) SKIN CRACKED AT HILOC FASTENERS ATTACHING SKIN TO AFT FLANGE OF WING ATTACH FITTING. CONDITION EVIDENT ON BOTH LT AND RT SKINS OF WING CENTER SECTION.  MFG HAS A FIELD REPAIR TO DEAL WITH THESE CRACKS. CRACKS FOUND VISUALLY WITH WING BOLT COVERS REMOVED. (TC NR 20060502000)                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L72 3T4  T  A14CE   E4EA    5  CSTC      
20060623001902006062300190EU  2006       6          23         CA060502002      120060427G2497                WIRE                                    AIRBUS310   A310304     3930339EU  GE    CF6   CF680C2A5        NE                                              BURNED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING ROUTINE INSPECTION, FOUND THE ELECTRICAL OUTLET WIRE FIN 8ME CHAFED ON FRAME 17 BETWEEN STR 28 AND 29 RT SIDE. THE GROMMET PROTECTION HAD FALLEN OFF FROM THE FRAME AND WIRE WAS HANGING ON THE FRAME WITH THE RESULT OF ARCING AND FRAME DAMAGE. THE WIRING AND FRAME WAS REPAIRED. A FLEET CAMPAIGN HAS BEEN INITIATED TO INSPECT THIS AREA ON ALL A-310.  (TC NR 20060502002)                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  FRTA35EU   E13NE                
20060626000632006062600063EU  2006       6          26         CA060502003      120060422G3397                WIRE                                    AIRBUS310   A310304     3930339EU  GE    CF6   CF680C2A5        NE                              NAV LIGHT       BURNED          W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA                                                                      (CAN) DURING AIRCRAFT TOWING, THE NAV 2 POSITION LIGHT CB POPPED. UNABLE TO RESET. DURING INVESTIGATION, FOUND THE 4 WIRES FROM THE LIGHT UNIT ASSY (7LA) BURNED ABOUT 8 INCHES LONG. WIRING WAS REPLACED AND LIGHT ASSEMBLY AND RELAY WERE REPLACED AS PRECAUTIONARY MEASURE. SB 30-0627-33-SB01 WILL BE INCORPORATED IN ALL AIRCRAFT TO UPGRADE THE NAVIGATIONAL LIGHT SYSTEM AND PREVENT THIS TYPE OF PROBLEM. (TC NR 20060502003)                                                                                                                                                                                                                                                                                                           2L72 4F4  FRTA35EU   E13NE                
20060703000032006070300003NE  2006       7          3          CA060502004      220060424G72503020159         SHROUD                                                                     PWA   PT6   PT6A135     52043NE                              TURBINE         DISTORTED       W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                          PCE35094                    DURING HOT SECTION KIT REPAIR OF A PT6A-135 ENG, CT SHROUD SEGMENT-RETAINING RING WAS FOUND LOOSE AND PARTIALLY DISENGAGED FROM CT SHROUD HOUSING RETAINING GROOVE.  MINOR SHIFTING OF CT SHROUD SEGMENTS WERE NOTED (SEE PHOTOGRAPH NR 1 AND 2). THE CT SHROUD SEGMENT-RETAINING RING (P/N 3020159) WAS OF PRE SB 1627 CONFIG AND CT SHROUD SEGMENTS (P/N 3053094) WERE OF PRE SB 1628 CONFIGURATION QTY 7-RUB SPOTS WERE NOTED ON THE CT SHROUD SEGMENTS WITH RUB ON CT BLADES.  CT SHROUD SEGMENT-RETAINING RING WAS FOUND DISTORTED AND PARTIALLY DISENGAGED FROM THE RETAINING GROOVE OF CT SHROUD HOUSING.  NO OVER HEATING/BURNING OF HOT SECTION PARTS NOTED.  INSPECTION OF CT SHROUD HOUSING WAS DONE AND ROUNDNESS OF ALL CRITICAL DI       4  T          E4EA                 
20060703000042006070300004    2006       7          3          CA060502005      120060428G3240266278          BRAKE ASSY                                                                                                                              MLG             DAMAGED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       2855 658                                                       FOLLOWING MX ONE OF OUR AME NOTICED THAT ONE OF OUR SPARE BRAKE ASSY P/N 2-1605-2 S/N 0378 MADE BY GOODRICH SEAM DIFFERENT FROM THE ONE REMOVED FROM THE A/C.  THE REMOVED BRAKE SHOWN 2 INNER SUPPORT FLANGE OF .5 INCH AND THE SPARE ONE SHOWN ONE SINGLE FLANGE OF 1.375 INCHES.  THE DOUBLE FLANGE IS WELL IDENTIFIED ON THE MANUFACTURER CMM BUT NO SPECIFICATION OF THE SINGLE ONE.  THE MANUF REQUIRED THE UNIT FOR INVESTIGATION.  ON THE PRELIMINARY STATUS THIS UNIT IS NOT PER MANUF SPEC DRAWING.  INVESTIGATION STILL IN PROGRESS.  THIS BRAKE ASSY IS SHOWING THE FOLLOWING DATA, P/N 266-278 CHG C,  P/N 260-903 CHG B, S/N 0378 DATE OF MAN 08-01, INSP NR 04-90.                                                                                                         
20060720003212006072000321EA  2006       7          20         CA060502006      120060430G29136307901         PUMP                                    DHAV  DHC4  DHC4A       2800304EA                                                               HYDRAULIC SYS   FAILED          W      O   OTHER                                                                                           JF WARNING INDICATION        FLT CONT AFFECTED                                   CRCRUISE         1                      CA                                                                      AFTER REPLACING A PUMP DUE TO TIME-EX, NEXT 3 PUMPS INSTALLED FAILED.  ALL FAILED DUE TO SHAFT SHEARING.  FILTERS PULLED AFTER 1ST FAILURE, THERE WAS ONLY TRACE EVIDENCE OF METAL AND NOTHING ELSE.  FILTER WAS CLEANED, REINSTALLED IAW MM.  AFTER NEXT 2 FAILURES FILTERS PULLED AGAIN WITH NO METAL FINDINGS.  FIRST FAILED PUMP, DISASSEMBLED IT TO TRY AND FIND CAUSE FOR FAILURE.  DISASSEMBLY FOUND 2 OF PISTONS SEIZED DUE TO OVERHEATING AND SEPARATED FROM SWASH PLATE.  1 PISTON HAD END TORN OFF AND HAD GENERATED A FAIR AMT OF METAL CONTAM INTERNALLY TO PUMP.  STILL INVESTIGATING CAUSE OF OVERHEATING THAT FAILED ORIG PUMP.  UNABLE TO CHECK OTHER 2, SHIPPED ALREADY.  AWAITING THE REPAIR SHOPS REPORT.                   2H72 4R      1A19                         
20060705000312006070500031    2006       7          5          CA060502008      420060427G2562MN1300          BATTERY         ACK                     PIPER PA34  PA34200T    7103406SO  CONT  O360  TSIO360E    17025SO  HARTZLHCC2Y BHCC2YF2    GL  ELT             LEAKING         W      O   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      CA       5          026049                                              (CAN) ELT BATTERIES LEAKED. (TC NR 20060502008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L72 3O3  O  A7SO    E9CE    5  CP920     
20060703000372006070300037SW  2006       7          3          CA060503001      120060426G2997212075369001    WIRE                                    BELL  212   212         1181420SW  PWA   PT6T  PT6T3       52045EA                              CLOG INDICATOR  BROKEN          W      O   OTHER                                                                                           N  FALSE WARNING                                                                 NRNOT REPORTED   1                      CA       181                                                            DURING ROUTINE INSPECTION, THE INDICATOR WAS SHOWING RED INDICATING FILTER BYPASS CONDITION.  UPON INVESTIGATION BY AME NONE OF THE FILTERS HAD BYPASSED ON THE INTEGRATED VALVE AND FILTER ASSEMBLY.  AT THIS TIME IT WAS DETERMINED THAT THE CLOGGING INDICATOR WAS THE PROBLEM AND THIS WAS REPLACED AND FUNCTION CHECKED OK.  6.1 HOURS LATER THE SAME CONDITION WAS NOTICED ON THE CLOG INDICATOR AND THE WIRES WERE FOUND TO HAVE BROKEN OFF.  THE WIRES WERE SOLDERED BACK AND INDICATOR REPLACED AT A LATER DATE.                                                                                                                                                                                                                       1G71 4U4  U  H4SW    E22EA                
20060703000382006070300038CE  2006       7          3          CA060503002      120060501G243523078019        STARTER GEN                             BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE  HARTZLHCE4A HCE4A3I     NE  LT ENGINE       SEIZED          W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA            30704                                                     IN CRUISE, LT GEN FAIL LIGHT ILLUM.  ATTEMPT TO RESET GEN, IT WOULD NOT COME ON LINE.  AFTER GEN FAILURE, LT ENG FIRE WARN IND ALSO CAME ON.  LT ENG WAS SHUT DOWN AND ENG FIRE BOTTLE WAS DISCHARGED AS PER RELATED CHECKLIST.  LANDED SAFELY.  MX INSPECTED A/C, FOUND LT STARTER-GEN FAILED INTERNALLY AND PAINT ON UNIT BLISTERED INDICATING IT HAD DRASTICALLY OVERHEATED.  INVESTIGATION REVEALED STARTER-GEN DRIVE SPLINE HAD SHEARED.  APPROPRIATE INSPECTIONS CARRIED OUT PER MM.  STARTER GEN AND FIRE BOTTLE REPLACED, A/C RETURNED TO SERVICE.  FIRE WIRE IS LOCATED IN CLOSE PROX STARTER-GEN.  STARTER-GEN INSTALLED PREV DAY IN REPAIRED CONDITION, AT TIME OF FAILURE STARTER-GEN HAD ONLY ACCUMULATED 1.6 HOURS SINCE REPAIR.  2L72 4T4  TRTA24CE   E26NE   5  CP10NE    
20060703000392006070300039CE  2006       7          3          CA060503003      120060501G243523078019        STARTER GEN                             BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE  HARTZLHCE4A HCE4A3I     NE  LT ENGINE       FAILED          W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      IN CRUISE, LT GEN FAIL LIGHT ILLUM.  CREW ATTEMPT RESET, GEN BUT WOULD NOT COME ON LINE.  AFTER GEN FAILURE,  LT ENG FIRE WARNING INDICATION ALSO CAME ON.  LT ENG WAS SHUT DOWN AND ENG FIRE BOTTLE DISCHARGED PER CHECKLIST.  A/C LANDED SAFELY.  MX INSPECT A/C AND FOUND LT STARTER-GEN FAILED INTERNALLY AND PAINT ON UNIT WAS BLISTERED INDICATING DRASTICALLY OVERHEATED. INVESTIGATION REVEALED, STARTER-GEN DRIVE SPLINE SHEARED.  INSPECTIONS PER MM.  STARTER GEN AND FIRE BOTTLE REPLACED, A/C RETURNED TO SERVICE.  FIRE WIRE IS LOCATED IN CLOSE PROXIMITY TO STARTER-GEN.  STARTER-GEN INSTALLED PREVIOUS DAY IN A REPAIRED CONDITION, AT TIME OF FAILURE STARTER-GEN HAD ONLY ACCUMULATED 1.6 HOURS SINCE REPAIR.               2L72 4T4  TRTA24CE   E26NE   5  CP10NE    
20060626000102006062600010CE  2006       6          26         CA060503004      120060501G2435                SHAFT           LEARSIEGLER             BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE  HARTZLHCE4A HCE4A3I     NE  STARTER GEN     SHEARED         W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA            307   94094                                               IN CRUISE, LT GEN FAIL LIGHT ILLUMINATED.  ATTEMPTED TO RESET GEN BUT IT STILL WOULD NOT COME ON LINE.  SHORTLY AFTER GEN FAILURE, LT ENG FIRE WARNING IND ALSO CAME ON.  LT ENG WAS SHUTDOWN AND ENG FIRE BOTTLE WAS DISCHARGED.  MX INSPECTED A/C. FOUND LT STARTER GEN HAD FAILED INTERNALLY AND PAINT ON UNIT WAS BLISTERED INDICATING IT HAD DRASTICALLY OVERHEATED.  ALSO REVEALED STARTER GEN DRIVE SPLINE HAD SHEARED.  INSP CARRIED OUT IAW MM.   STARTER GEN, FIRE BOTTLE WERE REPLACED, AND A/C RETURNED TO SERV.  NOTED FIRE WIRE IS LOCATED IN CLOSE PROX TO STARTER/GEN.  STARTER/GEN WAS INSTALLED PREVIOUS DAY IN A REPAIRED CONDITION, AT TIME OF FAILURE STARTER/GEN HAD ONLY ACCUMULATED 1.6  HRS SINCE REPAIR.              2L72 4T4  TRTA24CE   E26NE   5  CP10NE    
20060703000402006070300040NM  2006       7          3          CA060503007      120060427G5270AE4888100       SWITCH                                  BOEING727   727223      1384074NM  PWA   JT8   JT8D15A     52051NE                              CARGO DOOR      FAILED          W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CRCRUISE         1                      CA                                                                      AT FL380, MAIN CARGO DOOR LIGHT ILLUMINATED ACCOMPANIED BY "LATCH LOCK PIN NOT ENGAGED" ON DOOR CONTROL PANEL.  A/C TURNED BACK AND DURING DESCENT LIGHTS REMAINED ILLUMINATED UNTIL CABIN PRESSURE WAS REDUCED TO MINIMUM AT WHICH POINT BOTH LIGHTS HAVE EXTINGUISHED. UPON ARRIVAL, MAINTENANCE FOUND THAT FORWARD LATCH PIN MICRO-SWITCH TRIGGER PLATE COTTER PIN WAS INFERRING WITH A RIVET TAIL ON THE DOOR SKIN DOUBLER. THIS WAS A POSSIBLE CAUSE FOR DOOR INDICATION. AFTER ACCESS TO THE AREA WAS PROVIDED BY REMOVING THE ACCESS PANEL, TRIGGER PLATE WAS FREED UP BY REPOSITIONING THE COTTER AND OPERATIONALLY CHECKED SERVICEABLE. SWITCH AND PLATE ASSY REPLACED AS A PRECAUTION.                                                2L73 4F4  F  A3WE    E2EA                 
20060703000412006070300041NE  2006       7          3          CA060503008      220060428G7310                B-NUT                                   SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1        NE                              ENGINE FUEL     LOOSE           W      E   ENGINE SHUTDOWN                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      TXTAXI/GRND HDL  1                      CA                                                                      DURING T/S OF START SYS OF SISTER A/C, START INJECTOR ON RT SIDE OF ENG WAS REMOVED FOR COMPARISON INSPECTION.  AFTER INSPECTION ORIG INJECTOR WAS INSTALLED.   NO CROSS CHECK INSPECTION, NOR GROUND-RUN WERE COMPLETED.  NEXT DAY PILOT NOTED A STAGNATED/HUNG START, AND ADVANCED THROTTLE TO EMERG POSITION TO LIGHT OFF ENGINE.  ENG WAS THEN SHUT DOWN AND MX WAS CALLED.  ENGINEER ON SITE GOT PILOT TO  ATTEMPTED ANOTHER START AND VISUALLY NOTICED SPRAYING FUEL IN ENG BAY, START WAS ABORTED.  UPON CLOSE INSPECTION, B-NUT ON START INJECTOR LINE WAS FOUND TO HAVE NO TQE AND LOOSE ON TEE FITTING.  TIGHTENED LINE TO PROPER TQ AND THE START WAS ATTEMPTED AGAIN.   PERFORMED START/GROUND-RUN/LEAK CHECK ALL SYSTEMS FUNCTIONIN1G71 3U3  U  H9EU    E19EU                
20060703000422006070300042CE  2006       7          3          CA060503009      120060402G7800780000          EXTRACTOR                               BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA                              EXHAUST GAS     CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      DURING INSPECTION THE ENGINEER NOTICED A CRACK IN ONE OF THE EXHAUST GAS EXTRACTORS.  FURTHER INVESTIGATION ON THE REMAINING EXHAUST GAS EXTRACTORS REVEALED CRACKS AS WELL.  THE PARTS WERE REPAIRED AND REINSTALLED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L72 4T4  T  A24CE   E4EA                 
20060703000432006070300043EA  2006       7          3          CA060503010      120060420G5610601R3303318     WINDSHIELD                              CNDAIRCL600 CL6002C10   1390015EA  GE    CF34  CF348C1          NE                              COCKPIT         CRACKED         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         DEDESCENT        1                      CA                                                                      RIGHT FORWARD WINDSHIELD CRACKED DURING DESCENT FROM 350 TO 330.  REMOVED AND INSTALLED F/O'S WINDSHIELD.  RIGHT FORWARD WINDSHIELD CRACKED DURING DESCENT FROM 350 TO 330.  REMOVED AND INSTALLED F/O'S WINDSHIELD.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F4  FRTA21EA   EOOO63EN             
20060719000152006071900015    2006       7          19         CA060504001      220060317G7321442324          HMU                                     BOMBDRBD700 BD7001A10   1390006GL                                                               LT ENGINE       ACTIVATED       W      C   ABORTED TAKEOFF                                                                                 R  PARTIAL RPM/PWR LOSS                                                          TXTAXI/GRND HDL  1                      CA       173                                                            (CAN) CREW TAXIED OUT,TESTED THRUST REVERSER JUST PRIOR TO TAKEOFF.  PLACED BOTH PWR LEVERS IN T/O DETENT, STARTED T/O ROLL.  FELT AC SWERVE LT OF CTR LINE.  CREW NOTICED LT ENG WAS STILL AT IDLE WITH PWR LEVER IN TAKEOFF DETENT.  CREW ABORTED TAKEOFF.  NO EICAS MESSAGES WERE POSTED DURING THIS EVENT.  LT AND RT N1 BUGS BOTH TARGETED T/O PWR ON DISPLAY DURING THIS EVENT.  CREW TAXIED OFF RUNWAY.  CREW TRIED TO RUN-UP LT ENG ON RAMP, IT WOULD NOT ACCELERATE. NO EICAS MESSAGES POSTED. CHECKED TIME LIMITED DISPATCH, STATUS CLEAR FOR LT ENG.  LT ENG EEI DOWNLOAD REVEALED THAT HMU METERING VALVE DID NOT APPEAR TO RESPOND TO THRUST COMMAND.  HMU REMOVED AND REPLACED.  BOTH ECU'S ALSO REPLACED.  (TC NR 20060504001)   2L72 4F    RTT00003NY                     
20060703000972006070300097EA  2006       7          3          CA060504002      120060327G27304006719904      DRIVE ASSY                              DHAV  DHC7  DHC7102     2802708EA  PWA   PT6   PT6A50      52043EA  HAMSTD24PF  24PF305     GL  ELEVATOR SERVO  FAILED          W      O   OTHER                                                                                           FE FLT CONT AFFECTED         VIBRATION/BUFFET                                    CLCLIMB          1                      CA                                                                      CLIMB TO FL 120, AT FL 085 COMMUNICATION ESTABLISHED WITH APPROACH, AND INSTRUCTED TO MAINTAIN FL 080.  CAPT TOLD GO TO DESCENT AND MAINTAIN 080, AUTOPILOT WAS ENGAGED, CAPT REALIZED A/C WAS STILL CLIMBING AND THE WHEEL TRIM WAS TRIMMING FULL NOSE-UP, FO PUSHING ON CONTROL COLUMN, CAPT IMMEDIATELY DISENGAGE AUTO-PILOT, RESULT WAS A SUDDEN PITCH ATTITUDE CHANGE, A/C STARTED TO VIBRATE AND A VERY SCARY MOVEMENT OF A/C FOLLOWED.  FLT RESUMED NORMALLY AFTERWARD, AND LANDED SAFELY AT AIRPORT. THE FOLLOWING WAS CARRIED OUT TO T/S & RECTIFY SNAG.  AUTO-PILOT FUNCTION CHECKED, FOUND TOUCH CONTROL STEERING NOT WORKING.  AUTO-PILOT COMPUTER REPLACED, ELEVATOR SERVO REPLACED, AS PER MM 22-10-00.  AUTO-PILOT FUNCTION CHECK2H74 4T4  T  A20EA   E4EA    6  CP1NE     
20060703001082006070300108GL  2006       7          3          CA060504003      220060428G726023005747        BEARING CAGE    ALLSN       23005655                                       ALLSN 250C  250C30P     03013GL                              GEARBOX         FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       6078       CAG95018                                            BEARING, REMOVED FROM GEARBOX DURING 3500 HOURS INSPECTION, HAS BEEN PREVIOUSLY ASSEMBLED WITH ONE BALL NOTICEABLY SMALLER THAN THE OTHER BALLS IN THE BEARING ASSEMBLY.  REF ROLLS-ROYCE IPC, 14W4, 72-60-00, FIG.2, P.5, ITEM 39.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    3  U          E1GL                 
20060703001092006070300109SO  2006       7          3          CA060504004      220060426G7200                ENGINE                                  DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO                                              FAILED          W      A   UNSCHED LANDING                                                                                 YJ ENGINE STOPPAGE           WARNING INDICATION                                  APAPPROACH       1                      CA                                                                      ENGINE QUIT ON APPROACH, ONCE LANDED THE PILOT RESTARTED THE ENGINE AND TAXIED TO THE PARKING AREA.  THE AIRCRAFT WAS INSPECTED AND IT SEEMS TO BE FUEL PRESSURE THAT WAS THE CAUSE OF THE ENGINE FAILURE.  RIGGING AND MULTIPLE TESTS WERE CONDUCTED AND THE PROBLEM DID NOT RE-APPEAR.                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L71 3O3  ONTTA4CH   E7SO                 
             20080520         2008       5          20         CA060504005      420060421G2562GS21            BATTERY                                 AYRES S2    S2RR1820    0970215SO  WRIGHTR1820 R182099     67020EA  HAMSTD23E   23E50       NE  ELT             UNSERVICEABLE   W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) FOUND CORROSION AROUND BATTERY. (TC NR 20060504005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L71 4R4  R  A4SW    5E10    6  CP603     
20060703001102006070300110CE  2006       7          3          CA060504006      120060503G552011561010325     TORQUE TUBE                             BEECH 100   B100        1152919CE  GARRTTTPE331TPE3316252B 01514WP  HARTZLHCB4T HCB4TN5     GL  ELEVATOR        WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       176                                                            WHILE CHECKING THE ELEVATOR SYSTEM FOR FREEDOM OF MOVEMENT, EXCESSIVE PLAY WAS NOTICED IN THE LEFT ELEVATOR.  THE PLAY WAS ISOLATED TO THE ELEVATOR TORQUE TUBE FITTING.  THE TORQUE TUBE WAS REPLACED WITH A NEW ASSEMBLY. THE TORQUE TUBE WAS INSPECTED AND FOUND TO HAVE OVER-SIZED TAPER PINS INSTALLED FROM THE MANUFACTURE.                                                                                                                                                                                                                                                                                                                                                                                                               1L72 4T4  T  A14CE   E2WE    6  CP40EA    
20060703001112006070300111EA  2006       7          3          CA060504007      120060425G2760600913563       BRACKET                                 CNDAIRCL604 CL604       1900301EA  GE    CF34  CF34*            NE                              TRANSMITTER     FRACTURED       W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       3261                                                           PRIOR TO A/C DEPARTURE, AND DURING A GROUND CHECK OF THE FLIGHT SPOILERS, THE LT SPOILER INDICATED IT WAS EXTENDED WHILE SURFACE WAS PHYSICALLY IN STOWED POSITION (AS COMMANDED BY SPOILER LEVER).  FLIGHT SPOILER POSITION TRANSMITTER WAS INSPECTED AND FOUND TO BE LOOSE.  MAINTENANCE SECURED TRANSMITTER, AND ITEM WAS DEFERRED IN ACCORDANCE WITH  MEL.  BRACKET WAS REPLACED UPON RETURN IN ACCORDANCE WITH AMM.  BRACKET WAS FOUND WITH FRACTURES IN TWO PLACES ON BORE OF PART.                                                                                                                                                                                                                                                       2L72 4F4  FRTA21EA   E15NE                
20060703001122006070300112SW  2006       7          3          CA060504008      120060503G6410206016201131    BLADE                                   BELL  206   206L1       1182107SW  ALLSN 250C  250C28B     03013GL                              TAIL ROTOR      OUT OF TOLERANCEW      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       548                                                            THE BLADE WAS SENT TO ROTOR BLADES INCORPORATED FOR INSPECTION AS REQUIRED BY ASB 206L-04-127 REVISION C PART 3 AND BY AD CF-2004-05R1 PART D. ROTOR BLADES INCORPORATED HAS REPORTED THAT THE BLADE HAS FAILED THE INSPECTION AND IS BELOW TOLERANCE.  THE BLADE IS HELD FOR DISPOSAL AT ROTOR BLADES INCORPORATED AT THE REQUEST OF BELL HELICOPTER.  ROTOR BLADES INCORPORATED HAS PROBABLY FILED AN SDR IN THE USA.                                                                                                                                                                                                                                                                                                                         1G71 3U3  U  H2SW    E1GL                 
20060705000012006070500001EA  2006       7          5          CA060504009      220060504G852076097           CAMSHAFT        LYC         O320E2A     PIPER PA28  PA28140     7102802SO  LYC   O320  O320E2A     41508EA                              ENGINE          DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2069       L1929227A                                           CYLINDERS REMOVED FOR ON CONDITION INSPECTION, CAMSHAFT FOUND TO HAVE SEVERE CORROSION AND DAMAGE TO ALL LOBES.  ENGINE DISASSEMBLED FOR OVERHAUL, AND THE FOLLOWING WAS FOUND; BOTH INTAKE LOBES ON CAMSHAFT DESTROYED, ALL TAPPET BODIES DAMAGED, OIL PUMP HOUSING P/N 78528 DAMAGED BEYOND REPAIR, AND OIL PUMP IMPELLERS DAMAGED.  ALL INTERNAL COMPONENTS OF THE ENGINE HAD MINOR DAMAGE FROM METAL CONTAMINATION IN THE OIL.                                                                                                                                                                                                                                                                                                              1L71 3O3  O  2A13    E274                 
20060705000042006070500004CE  2006       7          5          CA060505003      120060505G5712                RIB                                     CESSNA185   185F        2072820CE                                                               LT WING         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      RIB ASSEMBLY ON WING CRACKED AT ATTACHMENT POINT TO SPAR.  SPAR WAS UNDAMAGED BUT TRACK WAS REPLACED.  AIRCRAFT HAS 10870.3 HOUR ON IT AT TIME OF REPAIR POSSIBLE TIME FATIGUED PART.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1H71 3O      3A24                         
20060705000072006070500007SO  2006       7          5          CA060508001      220060504G7310630662          FUEL LINE       CONT        IO360G      CESSNA337   337G        2075730CE  CONT  O360  IO360G      17025SO  MCAULY2AF34CD2AF34C306  GL  REAR ENGINE     BROKEN          W      A   UNSCHED LANDING                                                                                 JR WARNING INDICATION        PARTIAL RPM/PWR LOSS                                CLCLIMB          1                      CA                  355960                                              SHORTLY AFTER TAKEOFF, THE PILOT OF A CESSNA 337 NOTICED THAT FUEL PRESSURE ON THE REAR ENGINE BEGAN TO DROP OFF AND THE ENGINE BEGAN TO RUN ROUGH. TURNED ON THE ELECTRIC BOOST PUMP AND THE ENGINE CONTINUED TO RUN NORMALLY.  ELECTED TO RETURN TO THE AIRPORT AND LANDED WITHOUT INCIDENT.  AN INSPECTION OF THE REAR ENGINE REVEALED A BROKEN FUEL INJECTOR LINE FOR THE NUMBER SIX CYLINDER.  THE LINE HAD SEVERED COMPLETELY OFF FROM THE FUEL MANIFOLD SPIDER.  A SERVICEABLE LINE WAS INSTALLED AND LEAK CHECKS CARRIED OUT.  THE AIRCRAFT WAS RETURNED TO SERVICE.                                                                                                                                                                    1H72 3O3  O  A6CE    E1CE    5  CP5EA     
20060705000112006070500011NM  2006       7          5          CA060508002      120060506G561058935734        WINDOW                                  BOEING737   737522      138449FNM  CFMINTCFM56 CFM563C1    13802EU                              COCKPIT         CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         APAPPROACH       1                      CA                                                                      ON APPROACH FLIGHT, CREW REPORTED THAT THE FIRST OFFICERS NR 4 EYEBROW WINDOW HAD CRACKED.  ON ARRIVAL, WINDOW WAS INSPECTED AND REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F4  FRTA16WE   E21EU                
20060705000172006070500017NE  2006       7          5          CA060508003      220060508G7321CL12068161      RELAY                                   DHAV  DHC8  DHC8106     2809020NM  PWA   PW121 PW121       52124NE                              NR 1 ECU        DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      DURING A "C" CHECK INSPECTION, DURING THE OPERATIONAL CHECK OF "DUPLICATED ECU POWER SUPPLIES AND INTEGRITY OF DIODES CHECK" (TASK 73-20-02), THE BASE OF THE RELAY 7611-K3 (ENG NR 1 ECU) WAS FOUND UNGLUED.  WITH THIS RELAY DISCONNECTED, THE ECU OF THIS ENGINE GOES IN MANUAL MODE DUE TO THE FULL LOSS OF POWER.  IN ADDITION, THE FREE RELAY BASE RESULT IN A HI-RISK OF SHORTING WITH THE STRUCTURE.                                                                                                                                                                                                                                                                                                                                    2H72 4T4  TRTA13NM   E20NE                
20060705001122006070500112EU  2006       7          5          CA060508004      120060501G2932973811430       PRESSURE SWITCH                         PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  HYDRAULIC SYS   MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 S  AFFECT SYSTEMS                                                                CLCLIMB          1                      CA       10610                                                          AFTER TAKEOFF AND GEAR UP SELECTION WAS COMPLETED, THE CREW HAD A HYD. LIGHT ON THERE CAWS.  RETURNED AND UPON GEAR DOWN SELECTION THE GEAR MOTOR FAILED TO RUN.  GEAR DID A FREE FALL AND LOCKED DOWN.  ONCE IN HANGAR IT WAS NOTED THAT HYDRAULIC CONTROL CB WAS OUT.  CB WAS RESET AND THE DEFECT COULD NOT BE DUPLICATED.  PLEASE NOTE THIS AIRCRAFT HAD BEEN EXPERIENCING HYDRAULIC LIGHTS ON LANDING. (THIS NOTIFIED CREW THE PUMP HAD RUN MORE THAN SIX TIMES IN THE PAST HOUR OF FLIGHT) THIS DEFECT COULD NEVER BE DUPLICATED IN THE HANGAR EITHER.  MAINTENANCE REPLACED THE HYDRAULIC SYSTEM PRESSURE SWITCH AS A PRECAUTIONARY MEASURE AND NEITHER DEFECT HAS SINCE REOCCURRED.                                                     1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20060705001162006070500116NE  2006       7          5          CA060508006      220060508G7321CL12068161      RELAY                                   DHAV  DHC8  DHC8102     2809003NM  PWA   PW121 PW121       52124NE                              NR 2 ECU        SEPARATED       W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      DURING THE ACCOMPLISHEMENT OF THE TASK 7320/02 (OPERATIONAL CHECK OF DUPLICATED ECU POWER SUPPLIES AND INTEGRITY OF DIODES), THE 7611-K4 (ENG NR 2 ECU) RELAY BASE WAS FOUND UNGLUED.  THIS SITUATION REMOVED ALL THE POWER FOR THE ECU AND LIVE THE ENGINE IN MANUEL MODE.  IN ADDITION, THE FREE RELAY BASE GIVE THE OPPORTUNITY OF SHORTING TO THE ELECTRICAL PINS WITH THE ADJACENT STRUCTURE.                                                                                                                                                                                                                                                                                                                                              2H72 4T4  TRTA13NM   E20NE                
20060626001262006062600126SO  2006       6          26         CA060508007      120060418G271062701123        CONTROL CABLE                           PIPER PA44  PA44180     7104402SO  LYC   O360  O360A1H     41514EA  HARTZLHCC2Y HCC2YR2     GL  AILERON         FRAYED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      DURING EVENT INSPECTION OF DETAILED WING (RT) BROKEN STRANDS WERE OBSERVED ON RT AILERON BALANCE CABLE AS IT PASSED OVER A PULLEY AT WING STATION 22.00.  CABLE AND PULLEY WERE REMOVED.  CABLE WAS REPLACED NEW, PULLEY WAS CLEANED INSPECTED, LUBRICATED AND RETURNED TO SERVICE.  THERE IS VERY LITTLE CONTROL CABLE DEFLECTION OVER THE PULLEY'S IN THIS LOCATION.  ROUTINE CLEANING AND LUBRICATION OF PULLEY MAY FORESTALL CONTROL CABLE WEAR IN THIS AREA.                                                                                                                                                                                                                                                                               1L72 3O3  O  A19S0   E286    5  CP920     
20060626001282006062600128SO  2006       6          26         CA060508008      120060418G534386444800        SPAR                                    PIPER PA44  PA44180     7104402SO  LYC   O360  O360A1H     41514EA  HARTZLHCC2Y HCC2YR2     GL  NLG             CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3585                                                           DURING COMPLETION OF PIPER SB 1143 A 3/4" CRACK WAS OBSERVED RADIATING OUT FROM THE LOWER AFT BOLT HOLE OF THE NLG DRAG LINK TRUNNION MOUNTING.  FURTHER INVESTIGATION REVEALED A 1/2" CRACK RADIATING OUT FROM THE LOWER AFT BOLT HOLE OF THE RT DRAG LINK TRUNNION MOUNTING.  AIRCRAFT LT AND RT NOSE SPAR ASSEMBLIES WERE REPLACED NEW.                                                                                                                                                                                                                                                                                                                                                                                                      1L72 3O3  O  A19S0   E286    5  CP920     
20060626000112006062600011SO  2006       6          26         CA060508009      120060424G534386444800        SPAR                                    PIPER PA44  PA44180     7104402SO  LYC   O360  O360A1H     41514EA  HARTZLHCC2Y HCC2YR2     GL  FUSELAGE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       4063                                                           DURING COMPLETION OF SB1143, A 1 INCH CRACK WAS OBSERVED RADIATING OUT FROM THE LOWER AFT BOLT HOLE OF THE LT DRAG LINK TRUNNION MOUNTING.  FURTHER INVESTIGATION REVEALED A .5 INCH CRACK RADIATING OUT FROM LOWER AFT BOLT HOLE OF RT DRAG LINK TRUNNION MOUNTING.  AIRCRAFT LT AND RT NOSE SPAR ASSEMBLIES WERE REPLACED NEW.                                                                                                                                                                                                                                                                                                                                                                                                                1L72 3O3  O  A19S0   E286    5  CP920     
20060626000122006062600012SO  2006       6          26         CA060508010      120060418G57127847506         RIB                                     PIPER PA44  PA44180     7104402SO  LYC   O360  O360A1H     41514EA  HARTZLHCC2Y HCC2YR2     GL  WS 49.25        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3599                                                           DURING COMPLETION OF INSPECTION REQUIRED SB 1161, A 2 INCH LONG CRACK WAS OBSERVED IN THE LT WING RIB AT STN 49.25.  THE CRACK WAS LOCATED IN THE BEND RADIUS UNDER THE MAIN LANDING GEAR (MLG) SIDE BRACE ASSEMBLY (PN 95643-08).  A NEW RIB WAS INSTALLED.  BEFORE RE-INSTALLATION SHARP CORNERS ON THE SIDE BRACE MOUNT WERE POLISHED TO REDUCE THE POSSIBILITY OF CHAFING THE RIB IN THE AFFECTED AREA.                                                                                                                                                                                                                                                                                                                                     1L72 3O3  O  A19S0   E286    5  CP920     
20060626000132006062600013SO  2006       6          26         CA060508011      120060418G57127847507         RIB                                     PIPER PA44  PA44180     7104402SO  LYC   O360  O360A1H     41514EA  HARTZLHCC2Y HCC2YR2     GL  WS 49.25        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3599                                                           DURING COMPLETION OF INSPECTION REQUIRED SB 1161, A 3 IN LONG CRACK WAS OBSERVED IN THE RT WING RIB AT STN 49.25.  THE CRACK WAS LOCATED IN THE RIB BEND RADIUS UNDER THE MLG SIDE BRACE MOUNT (PN 95643-09).  A NEW RIB WAS INSTALLED.  BEFORE RE-INSTALLATION SHARP CORNERS ON SIDE BRACE MOUNT WERE POLISHED TO REDUCE THE POSSIBILITY OF CHAFING WITH THE RIB IN THIS AREA.                                                                                                                                                                                                                                                                                                                                                                 1L72 3O3  O  A19S0   E286    5  CP920     
20060626000142006062600014SO  2006       6          26         CA060508012      120060424G57127847507         RIB                                     PIPER PA44  PA44180     7104402SO  LYC   O360  O360A1H     41514EA  HARTZLHCC2Y HCC2YR2     GL  WS 49.25        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       4099                                                           DURING COMPLETION OF INSPECTION REQUIRED BY PIPER SB 1161, A 2.5 INCH LONG CRACK WAS OBSERVED IN THE RT WING RIB AND 3 INCH LONG IN THE LT WING RIB AT STN 49.25.  THE CRACKS WERE LOCATED IN THE BEND RADIUS UNDER THE MLG SIDE BRACE MOUNT (PN 95643-09).  NEW RIBS WERE INSTALLED.  BEFORE RE-INSTALLATION SHARP CORNERS ON SIDE BRACE MOUNT WERE POLISHED TO REDUCE THE POSSIBILITY OF CHAFING THE RIBS IN THIS AREA.                                                                                                                                                                                                                                                                                                                       1L72 3O3  O  A19S0   E286    5  CP920     
20060705001912006070500191WP  2006       7          5          CA060508013      120060506G6730                SEAL            ROBSIN      D2121       ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              SERVO           LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       731        4655                                                (CAN) SERVO FOUND TO HAVE AN EXCESSIVE OIL LEAK FROM THE UPPER SEAL.  THE SERVO WAS REPLACED WITH A SERVICEABLE UNIT.  THIS SERVO HAD BEEN REMOVED 109.4 HOURS BEFORE FOR A SEAL LEAK.  THE SERVO WAS RETURNED AT THAT TIME TO MFG FOR REPAIR. (TC NR 20060508013)                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1G71 3O3  O  H11NM   1E4                  
20060705001922006070500192SW  2006       7          5          CA060508014      120060508G3213MS1699799       BOLT                                    AIRTRCAT802 AT802A      0390308SW  PWA   PT6   PT6A67      52043NE  HARTZLHCB5M HCB5MA3     GL  MLG             LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       189                                                            (CAN) DURING THE ACCOMPLISHMENT OF THE ANNUAL INSPECTION OF THE LANDING GEAR, MAINTENANCE STAFF NOTICED THAT THE LT IB AND RT OB TORQUE PLATES THAT SECURE THE BRAKE CALIPERS WERE LOOSE. THE 6 BOLTS TAHT SECURE THE TORQUE PLATES TO THE MAIN WHEEL AXLE ASSEMBLY WERE LOOSE CAUSING THE PLATES TO SHIFT AS THE WHEELS WERE ROTATED BACK AND FORTH. THE OTHER AIRCRAFT IN THE FLEET WILL BE INSPECTED TO ENSURE ALL THE BOLTS ARE TIGHT. (TC NR 20060508014)                                                                                                                                                                                                                                                                                  1L71 3T4  TNCA19SW   E26NE   6  CP44GL    
20060705001932006070500193CE  2006       7          5          CA060509000      120060501G53305012015682      SKIN                                    BEECH 90    C90A        1152911CE  PWA   PT6   PT6A21      52043EA  HARTZLHCB3T HCB3TN3     GL  FUSELAGE        WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) SKIN P/N 50-120156-82 (PRESSURE VESSEL) EXIBITING WEAR MARK ALONG FASTENER ROW ATTACHING FILLET P/N 50-420023-24 TO IT. WEAR MARK NOT READILY VISIBLE WITHOUT PULLING AWAY FILLET FROM SURFACE OF SKIN. WEAR MARK IS CAUSED BY LOOSENING OF FILLET TO SKIN FASTENERS AND SUBSEQUENT CHAFFING. UN-NOTICED, THIS CONDITION COULD LEAD TO PRESSURE VESSEL RUPTURE. (TC NR 20060509000)                                                                                                                                                                                                                                                                                                                                                       1L72 3T4  TRT3A20    E4EA    6  CP15EA    
20060705001952006070500195CE  2006       7          5          CA060509001      120060502G5753122101015       FLAP TRACK                              CESSNA185   A185F       2072821CE  CONT  O520  IO520D      17032SO  MCAULYD3A34 D3A34C403   GL  TE FLAPS        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) LT IB FLAP TRACK, FWD ANGLES, AGAINST SPAR FOUND CRACKED AT BEND RADIUS, LOWER END. (TC NR 20060509001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3O3  O  3A24    E5CE    5  CP47GL    
20060705001982006070500198CE  2006       7          5          CA060509002      120060428G3340S21604          SWITCH                                  CESSNA172   172N        2072434CE  LYC   O320  O320H2AD    41508EA  MCAULY1C160 1C160DTM    GL  LANDING LIGHT   DEFECTIVE       W      A   UNSCHED LANDING                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA                                                                      (CAN) PILOT WAS IN CRUISE WITH LANDING LIGHT ON, WHEN SHE SMELLED SMOKE AND NOTICED SMOKE COMING FROM LANDING LIGHT SWITCH. SMOKE STOPPED WHEN SWITCH TURNED OFF AND PILOT SQUAWKED 7700 FOR HELP AND SHE WAS ADVISED TO LAND. AGAIN IT WAS CONFIRMED THAT THE SWITCH WOULD SMOKE WHEN TURNED ON, BUT NOT WHEN OFF. PILOT FLEW AIRCRAFT HOME WITH LANDING LIGHT OFF, WHERE MAINTENANCE CONFIRMED PROBLEM AND REPLACED THE SWITCH.  NOTE: THIS IS NOT AN UNCOMMON PROBLEM WITH THESE SWITCHES. (TC NR0 20060509002)                                                                                                                                                                                                                              1H71 3O3  ONT3A12    E274    5  NP910     
20060705001992006070500199CE  2006       7          5          CA060509003      120060501G2410DOFF10300F      ALTERNATOR                              CESSNA150   150C        2071808CE  CONT  O200  O200A       17020SO                              ENGINE          DEFECTIVE       W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) STATOR AND RECTIFIER DEFECTIVE. (TC NR 20060509003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3O3  O  3A19    E252                 
20060705001172006070500117EU  2006       7          5          CA060509004      120060508G2434AN960JD616      WASHER                                  SAAB  SF340 340B        7860101EU  GE    CT7TP CT79B       30030NE  ROTOL R390  R3904123F27 NE  STARTER GEN     MELTED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       14635                                                          WHILE CONDUCTING A VISUAL INSPECTION OF THE PORT STARTER GENERATOR GROUND POINT SEALANT REMOVED.  IT WAS DISCOVERED THAT THE ALUMINUM WASHERS, P/N AN960JD616, BETWEEN THE GROUND POINT ATTACH BOLT AND THE BRACKET HAD MELTED.  THE GROUND POINT BRACKET SHOWED EVIDENCE OF ARCING AND THE GROUND POINT ATTACH BOLT SHOWED EVIDENCE OF CORROSION.  INSPECTION OF A SECOND AIRCRAFT C-GMNM S/N 340B-364 REVEALED CORROSION ON THE ALUMINUM WASHERS P/N AN960JD616.  AN INSPECTION OF THE BALANCE OF SAAB 340 FLEET IS ON GOING.                                                                                                                                                                                                                 2L72 4T4  TRTA52EU   E8NE    6  CP31NE    
20060705002882006070500288EA  2006       7          5          CA060509006      220060504G8530SL32006WAZOP    CYLINDER HEAD                           CESSNA172   172P        2072436CE  LYC   O320  O320D2J     41508EA  MCAULY1C160 1C160DTM    GL  ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1800                                                           (CAN) ONE CRACK RUNNING BETWEEN UPPER SPARK PLUG HOLE AND EXHAUST VALVE.  SECOND CRACK FROM LOWER SPARK PLUG HOLE EXTENDING APPROX 1 INCH INTO CYL HEAD. (TC NR 20060509006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H71 3O3  ONT3A12    E274    5  NP910     
20060711001212006071100121WP  2006       7          11         CA060509007      120060504G3213369H600131      STRUT                                   HUGHES369   369D        4470706WP  ALLSN 250C  250C20B     03013GL                              MLG             CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) WHILE DOING A 100 HOUR INSPECTION OF THE AIRCRAFT THE ENGINEER NOTICED SOME CRACKED PAINT ON THE BOTTOM SIDE OF THE STRUT EMINATING FROM THE LANDING GEAR BRACE BOLT HOLE.  HE THEN REMOVED SOME OF THE PAINT AND REVEALED A CRACK 1.5 INCHES LONG GOING OUTWARDS TOWARD THE LANDING GEAR DAMPER ATTACH POINT. (TC NR 20060509007)                                                                                                                                                                                                                                                                                                                                                                                                        1G71 3U3  U  H3WE    E4CE                 
20060705002892006070500289EU  2006       7          5          CA060509008      120060505G3320E033601         BALLAST                                 AEROSPATR42 ATR42300    8680920EU  PWA   120   PW120            NE  HAMSTD14SF  14SF5       NE  LIGHT           OVERHEATED      W      O   OTHER                                                                                           MB OVER TEMP                 SMOKE/FUMES/ODORS/SPARKS                            CRCRUISE         1                      CA                                                                      (CAN) LAMP SOCKET OVERHEATED AT BALLAST 27LG CAUSING SMOKE ODOR IN CABIN. (TC NR 20060509008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2H72 4T4  TRTA53EU   E20NE   6  CP7NE     
20060705001322006070500132NE  2006       7          5          CA060509009      220060414G72600235237790      CHIP DETECTOR                           SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1        NE                              ENGINE          SHORTED         W      O   OTHER                                                                                           N  FALSE WARNING                                                                 HOHOVERING       1                      CA       1649                                                           IN FLIGHT, THE PILOT NOTICED THE ENGINE CHIP LIGHT ILLUMINATE.  LANDED AND THE ENGINEER LOOKED AT THE CHIP DETECTORS AND NO METAL WAS FOUND.  THEN RE INSTALLED THE CHIP DETECTORS AND CARRIED OUT A GROUND RUN.  AFTER 10 MINUTES OF GROUND RUNNING ANOTHER CHIP LIGHT OCCURRED.  AFTER THE ENGINE COOLED OFF THE CHIP LIGHT WOULD GO OUT.   THE ELECTRICALLY OPERATED CHIP DETECTOR WAS FOUND TO CAUSE A LIGHT WHEN HOT AND THEM EXTINGUISH WHEN COOLED OFF.                                                                                                                                                                                                                                                                                  1G71 3U3  U  H9EU    E19EU                
20060705002902006070500290NE  2006       7          5          CA060510001      220060508G7314B8187B          PUMP                                    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              FUEL SYS        LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) PUMP WAS FOUND TO BE NOISY DURING ENGINE PRIMING.  WHEN THE PUMP WAS REMOVED THE HOUSING AROUND THE ELECTRIC MOTOR WAS ALSO FOUND TO BE LOOSE. (TC NR 20060510001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1G71 3O3  O  H11NM   1E4                  
20060705001332006070500133CE  2006       7          5          CA060510002      120060502G554124130015        RIB                                     CESSNA172   172RG       2072438CE  LYC   O360  O360F1A6    41514EA  MCAULY2D34C B2D34C220   GL  RUDDER          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       7635 7635                                                      AT A 100 HOUR INSPECTION A CRACK WAS FOUND UNDER THE LEFT INBOARD RUDDER BAR BLOCK, AT THE MOST FORWARD BOLT HOLE.  RUDDER BLOCK HAD ABNORMAL MOVEMENT.  CRACK COULD ONLY BEEN SEEN AFTER BLOCK WAS REMOVED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H71 3O3  O  3A17    E286    5  CP7EA     
20060705001342006070500134NE  2006       7          5          CA060510003      220060503G7321430128806       FCU                                     SNIAS 350   AS350BA     8680817EU  LYC   LTS101LTS101600A3 41560NE                              ENGINE          FAILED          W      E   ENGINE SHUTDOWN                                                                                 AM FLAME/FIRE                OVER TEMP                                           TXTAXI/GRND HDL  1                      CA       3283 1218                                                      ON SECOND START OF THE DAY, A FLAME WAS SEEN COMING OUT OF EXHAUST AND A RAPID INCREASE IN TURBINE OUTLET TEMPERATURE.  AFTER SEVERAL MINUTES, A SECOND ATTEMPT WAS GIVEN WITH SIMILAR RESULTS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1G71 3U3  UNCH9EU    E5NE                 
20060705001352006070500135EA  2006       7          5          CA060510004      220060510G7250                BLADE                                                                      PWA   PT6   PT6*        52043EA                              ENGINE          FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3721                                                           FAILED ENGINE SENT TO O/H SHOP WHERE ALL CT BLADES WERE FOUND DAMAGED/BROKEN.  SIGNIFICANT DOWNSTREAM DAMAGE WAS EVIDENT.  CAUSE OF CT BLADE FAILURE NOT DETERMINED BUT LUGS WERE BROKEN OFF THE CT STATOR AS A RESULT OF HEAVY CONTACT BETWEEN CT DISK AND CT STATOR.   ENGINE OEM IS CURRENTLY INVESTIGATING RECENT RASH OF CT BLADE FAILURES ON THIS PT6A-114 ENGINE FAMILY.                                                                                                                                                                                                                                                                                                                                                                        3  T          E2NE                 
20060705001362006070500136CE  2006       7          5          CA060510007      120060507G5220                SHAFT                                   BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE  HARTZLHCE4A HCE4A3I     NE  EMERGENCY EXIT  CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      INTERNAL CABIN PORTION OF PHASE 3 INSPECTION FOUND BOTH RT EMERG EXIT DOORS WOULD NOT OPEN FROM INSIDE.  BOTH DOORS WERE REMOVED VIA EXT HANDLE AND DISASSEMBLED, UPON INSPECTION, FOUND RT COUPLING P/N 129-514065-2 WAS MATED TO SHAFT P/N 129-514033-2 AT ALL TIMES.  HANDLE LINKAGE WAS REMOVED AND DISASSEMBLED.  FOUND THERE WAS JUST ENOUGH SURFACE CORROSION ON EXT SURFACE OF THE SHAFT AND INTERNAL SURFACE OF COUPLER TO KEEP EXTERIOR HANDLE ENGAGED AT ALL TIMES WHICH IN TURN USED THE OUTSIDE HANDLE AS A STOP WHEN TRYING TO OPEN THE EXIT FROM INSIDE.  COUPLER WAS REMOVED FROM THE SHAFT AND SURFACE CORROSION REMOVED.  UNIT WAS REASSEMBLED AND EMERG EXIT HANDLE FUNCTION TESTED SERVICEABLE.                             2L72 4T4  TRTA24CE   E26NE   5  CP10NE    
20060711001372006071100137    2006       7          11         CA060510009      120060508G8011629435          SHAFT           CONT                                                       CONT  O520  IO520MB     17032SO                              STARTER ADAPTER BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                  277948R                                             THREE GEAR TEETH BROKEN OFF AND MISSING.  ONE OTHER TOOTH CRACKED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     3  O          E5CE                 
20060626000162006062600016NE  2006       6          26         CA060510010      220060503G7200ARRIEL1D1       ENGINE                                  SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1        NE                                              MAKING METAL    W      E   ENGINE SHUTDOWN                                                                                 KBJFLUID LOSS                SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION        TXTAXI/GRND HDL  1                      CA       6081 92                            9135                        ON ENGINE STARTUP, THE PILOT NOTICED A FLICKERING ENGINE CHIP LIGHT, SECONDS LATER THE CHIP LIGHT CAME ON SOLID.  ENGINE WAS SEEN SMOKING AND OIL COMING FROM EXHAUST STACK.  ENGINE WAS SHUTDOWN AFTER APP 1 MINUTE OF OPERATION.  ENGINE HAS BEEN SENT TO OVERHAUL COMPANY FOR INVESTIGATION AND REPAIR.  ENGINE HAD 91.9 HOURS SINCE OVERHAUL.  ENGINE IS AT THE OVERHAUL COMPANY AT THE MOMENT AND A DETAILED REPORT WILL BE COMING AT A LATER DATE.                                                                                                                                                                                                                                                                                        1G71 3U3  U  H9EU    E19EU                
20060711001382006071100138CE  2006       7          11         CA060510011      120060502G32135041000206      TRUNNION                                CESSNA401   401B        207590ECE  CONT  O520  TSIO520EB   17040SO  MCAULY3AF32C3AF32C*     GL  RT MLG          CRACKED         W      O   OTHER                                                                                           K  FLUID LOSS                                                                    LDLANDING        1                      CA       12920                                                          THE RT MAIN LANDING GEAR OLEO WENT FLAT AFTER LANDING.  A CRACK WAS NOTICED ON THE UPPER TRUNNION, JUST UNDER THE SIDE BRACE ATTACH FITTING.  THE UPPER TRUNNION WAS REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L72 3O3  O  A7CE    E8CE    5  CP22EA    
20060626000172006062600017SO  2006       6          26         CA060510013      120060509G551146530003        RIB                                     PIPER PA31T PA31T       7103124SO  PWA   PT6   PT6A28           EA  HARTZLHCB3T HCB3TN3     GL  HORIZONTAL STAB CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      DURING A ROUTINE INSPECTION, THE LT OB STABILIZER RIB WAS FOUND CRACKED NEAR THE HINGE ATTACH AREA.  THE RIB WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L72 3T4  T  A8EA    E4EA    6  CP15EA    
20060626000182006062600018WP  2006       6          26         CA060510014      120060503G2400B2804           RELAY                                   ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              GOVERNOR        STUCK           W      K   NONE                                                                                            N  FALSE WARNING                                                                 ININSP/MAINT     1                      CA       560                                                            THE GOVERNOR (OFF) WARNING LIGHT WAS STAYING ON, REGARDLESS OF THE STATUS OF THE GOVERNOR.  BY ALL CHECKS THE GOVERNOR WAS WORKING WHEN TURNED ON, AND TURNING OFF WHEN THE SWITCH WAS TURNED OFF, HOWEVER THE (GOVERNOR OFF) LIGHT STAYED ON AT ALL TIMES.  THE CONTROL RELAY FOR THE LIGHT WAS FOUND TO BE STICKING, KEEPING THE LIGHT ON.  RELAY WAS REPLACED, AND NO FURTHER DEFECTS WERE FOUND.                                                                                                                                                                                                                                                                                                                                            1G71 3O3  O  H11NM   1E4                  
20060711001392006071100139CE  2006       7          11         CA060511001      120060511G531012118061        DOOR FRAME                              CESSNA207   T207A       2073614CE  CONT  O520  TSIO520M    17040SO                              FUSELAGE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       13791                                                          .5 INCH CRACK FOUND IN LOWER LT DOOR POST JAMB DURING ROUTINE INSPECTION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3O3  O  A16CE   E8CE                 
20060711001402006071100140EU  2006       7          11         CA060511002      120060510G3520630130018       MANIFOLD                                AIRBUSA340  A340313            EU  CFMINTCFM56 CFM565C4    13802NE                              PAX OXYGEN      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      AIRCRAFT HAD 22 MANIFOLDS FOUND CRACKED.  LOOKED AT ANOTHER AIRCRAFT TO PROVIDE SPARES, BUT FOUND MOST OF ITS MANIFOLDS CRACKED TOO.  DRAGER (VENDOR) CONTACTED, AND WILL PROVIDE REPLACEMENTS.  MANIFOLD IS MADE OF A VARIETY OF PLASTIC, WHICH IS BRITTLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L74 4F4  FRTA197    E37NE                
20060711001412006071100141SW  2006       7          11         CA060511004      120060509G3211AN324A          BOLT            FRCHLD      2751500001  SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE33111U   01514WP  MCAULY4HFR344HFR34C652  NE  TRUNNION        SHEARED         W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      CA                  946                                                 PILOT REPORTED LOSS OF GREEN LIGHT AND TRANSIT LIGHT ON THE NOSE GEAR DURING TAXI INTO AIRPORT.  PILOT SHUTDOWN AC AND EMPTIED AIRCRAFT.  MAINTENANCE MOVED AIRCRAFT TO SAFE LOCATION AND WHILE JACKING THE AIRCRAFT NOTICED THAT NOSE WHEEL PIVOTED SIDEWAYS.  UPON INVESTIGATION IT WAS NOTED THAT THE UPPER GEAR TRUNNION PIN RETAINING BOLTS WERE SHEARED AND MISSING.  THEY WERE STILL IN PLACE YET THE HEADS WERE SHEARED OFF.  REMOVED AND INSPECTED THE LOWER PIN RETAINING BOLTS AND FOUND THEM CORRODED AND READY TO SHEAR.  ALL UNSERVICEABLE BOLTS REPLACED AND GEAR SWINGS CHECKED SERVICEABLE AND AIRCRAFT RETURNED TO SERVICE.                                                                                                   2L72 4T4  TRTA8SW    E4WE    6  C3PNE     
20060711001662006071100166CE  2006       7          11         CA060511005      120060414G533011443007529     SKIN                                    BEECH 1900  1900C       1154161CE  PWA   PT6   PT6A65B     52043EA  HARTZLHCB4M HCB4MP3     GL  FUSELAGE        CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) HEAVY CORROSION BETWEEN SKIN AND STRINGERS (BONDED) AT STRINGER SPLICES IN BELLY AT CENTERLINE STRINGER AND 2 LT AND RT OF CENTER. (TC NR 20060511005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4T4  TRTA24CE   E4EA    6  CP56GL    
20060711001852006071100185CE  2006       7          11         CA060511006      120060418G57301141200487374   SKIN                                    BEECH 1900  1900C       1154161CE  PWA   PT6   PT6A65B     52043EA  HARTZLHCB4M HCB4MP3     GL  WING            CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) OB FWD CORNER OF COLLECTOR TANK OPENING. SKINS P/N 114-120048-73 AND 74 FOUND CRACKED. HEAVY SKIN .071 (TC NR 20060511006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4T4  TRTA24CE   E4EA    6  CP56GL    
20060711001862006071100186SW  2006       7          11         CA060511007      120060509G32602751000305      STRIKER                                 FRCHLDSA227 SA227CC     3377522SW  GARRTTTPE331TPE33111U   01514WP  MCAULY4HFR344HFR34C652  NE  LT GEAR         LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) AFTER GEAR SWING TO CHECK FOR HYD LEAK IT WAS NOTED THAT THE LT GEAR DID NOT EXTEND.  THE LT OB STRIKER ON THE LT CAM ASSY WAS LOOSE AND NOT CONTACTING ACTUATOR AREA FOR UPLOCK RELEASE.  THE BOLT WAS REMOVED FROM STRIKER AND FOUND TO BE STRIPPED AND THE NUT HAD BACKED OFF CAUSING THE STRIKER TO BE VERY SLOOPY AND NOT CONTACTING THE ACTUATOR ARM ON UPLOCK INTERMITTANTLY. NEW BOLT AND NUT INSTALLED AND SWINGS ACCOMPLISHED SERVICIBLE.  AIRCRAFT RETURNED TO SERVICE. (TC NR 20060511007)                                                                                                                                                                                                                                    2L72 4T4  TRTA18SW   E4WE    6  C3PNE     
20060711001872006071100187CE  2006       7          11         CA060511008      120060426G573011412004854     DOUBLER                                 BEECH 1900  1900C       1154161CE  PWA   PT6   PT6A65B     52043EA  HARTZLHCB4M HCB4MP3     GL  WING            CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DOUBLER P/N 114-120048-54 FOUND CRACKED AT FWD OB CORNER. CAN NOT SEE CRACK UNLESS COLLECTOR FUEL TANK IS REMOVED. (TC NR 20060511008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4T4  TRTA24CE   E4EA    6  CP56GL    
20060711001882006071100188CE  2006       7          11         CA060511009      120060511G3230                LANDING GEAR                            BEECH 1900  1900C       1154161CE  PWA   PT6   PT6A65B     52043EA  HARTZLHCB4M HCB4MP3     GL                  MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) GEAR WAS RETRACTED AND GEAR HORN AND GEAR HANDLE LIGHT STAYED ON. (TC NR 20060511009)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4T4  TRTA24CE   E4EA    6  CP56GL    
20060711001892006071100189CE  2006       7          11         CA060512001      120060501G56203541029114      WINDOW                                  BEECH 58    58          1152740CE  CONT  O550  IO550C           SO  MCAULY3AF32C3AF32C512   GL  EMERGENCY EXIT  SEPARATED       W      A   UNSCHED LANDING                                                                                 D  INFLIGHT SEPARATION                                                           CLCLIMB          1                      CA       5338                                                           (CAN) EMERGENCY EXIT WINDOW OPENED ON TAKEOFF. WINDOW WENT FROM VENT POSITION TO EXIT POSITION INTO FREE AIR AND HINGE BROKE OFF AND WINDOW DETACHED FROM AIRCRAFT.   IT IS POSSIBLE THAT AT SOME PRIOR FLIGHT THE WINDOW WAS OPENED INCORRECTLY. WE HAVE OPERATED A FLEET OF 7 AIRCRAFT WITH THE SAME TYPE WINDOW WITH NO PRIOR PROBLEMS.  (TC NR 20060512001)                                                                                                                                                                                                                                                                                                                                                                                 1L72 3O3  O  3A16    E3SO    5  CP22EA    
20060719000222006071900022GL  2006       7          19         CA060512002      320060510G61124E220010        BOOT            HARTZL      HCB3TN3B    BEECH 99    99          1154002CE  PWA   PT6   PT6A28           EA  HARTZLHCB3T HCB3TN3     GL  BLADE DEICE     DEPARTED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                  BUA27150                            BUA27150        (CAN) DURING MAINT WALK AROUND,  COMPLETE PROP BLADE DE-ICE BOOT HAD DEPARTED AC. AIRFRAME, ENG WAS INSPECTED FOR FOD DAMAGE FROM DE-ICE BOOT. DETERMINED THAT BOOT HAD SEPERATED FROM AC DAY BEFORE DURING TAKE-OFF.  PILOT FELT VIBRATION FROM LT ENG DURING RUN-UP, DURING TAKE-OFF FLUCTUATION OF TORQUE INDICATION FOR ENG, THEN SETTLED OUT FOR REST OF FLIGHT BECAUSE VIBRATION WENT AWAY.  FURTHER INVESTIGATION SHOWS DE-ICE BOOT WAS THROWN ALONG LENGTH OF BLADE THEN DEPARTED AC (RUBBER STREAKS OUT TO BLADE TIP).  GLUE ON BLADE LOOKED TO BE IN NORMAL CONDITION, NO DETERIORATION OF GLUE BED.  DETERMINED 2 BOOTS ON THAT PROP WERE CHANGED, CANNOT DETERMINE IF IT WAS ONE OF  REPLACED BOOTS.                                1L72 3T4  T  A14CE   E4EA    6  CP15EA    
20060711001902006071100190EA  2006       7          11         CA060512003      120060509G3246C3US1563        BOLT                                    DHAV  DHC3  DHC3        2800202EA  GARRTTTPE331TPE33112UHR      WP  HARTZLHCB4T HCB4TN5     GL  RT WHEEL        FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       106                                                            (CAN) WHILE PERFORMING A 100 HOUR INSPECTION ON THE MLG WHEEL SKIS, MAINTENANCE FOUND THE RT WHEEL SKI ATTACH BOLT P/N:C3US156-3 TO BE BENT AND CRACKED.  BOLT ATTACHES THE SKI BRACKET ASSEMBLY LINK P/N: C3US108-34 TO THE MLG STRUT AND AXLE. THE BOLT HAS CRACKED AT THE START OF THE RADIUS WHERE THE DIAMETER OF THE BOLT CHANGES FRON .500 NR DIA TO .750 IN DIA IT APPEARS THAT THE CRACK OCCURED ON THE TOOLING MARK.  (TC NR 20060512003)                                                                                                                                                                                                                                                                                             1H71 3R4  T  A815    E4WE    6  CP40EA    
20060711001912006071100191GL  2006       7          11         CA060512006      120060508G7160C2E1079         FLAP                                    DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE  HAMSTD2D    2D30        NE  CARB HEAT       CRACKED         W      O   OTHER                                                                                           R  PARTIAL RPM/PWR LOSS                                                          TOTAKEOFF        1                      CA       23102                                                          (CAN) THE CARB HEAT FLAP ASSEMBLY HAD CRACKED UNDER THE DOUBLER PLATE, ALONG THE RIVET ATTCH LINE THAT CONNECTED THE FLAP/DOOR TO THE ACTUATING SHAFT BRACKET.    (TC NR 20060512006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1H71 3R3  RRCA806    5E1     5  CP206     
20060711001922006071100192CE  2006       7          11         CA060514001      120060513G322012436351        TORQUE LINK     CESSNA      1243800205  CESSNA207   207         2073602CE  CONT  O550  IO550F      17042SO  HARTZLHCJ3Y PHCJ3YF1    GL  NLG             CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2019 2019                                                      (CAN) NOSE LANDING GEAR UPPER TORQUE LINK FOUND CRACKED ON BOTH LT AND RT SIDE OF LWR WEB.  CRACK WAS DETECTED VISUALLY DURING 50 HR INSP AND LUBRICATION OF NOSE LANDING GEAR. THIS PART WAS INSTALLED NOVEMBER 2001, PREVIOUS PART HAD SAME CRACKS IN SAME LOCATION.  (TC NR 20060514001)                                                                                                                                                                                                                                                                                                                                                                                                                                                     1H71 3O3  O  A16CE   E3SO    5  CP36EA    
20060719000432006071900043SO  2006       7          19         CA060514002      220060511G8530TIST712ACA      CYLINDER HEAD                           CESSNA206   U206G       2073356CE  CONT  O520  IO520F      17032SO  HARTZLHCJ3Y PHCJ3YF1    GL  ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       798  798                           291018R                     (CAN) CYLINDERS NR 2 AND NR 4 WHERE FOUND TO BE CRACKED IN THE CYLINDER HEAD DURING A 200 HR INSPECTION. CYLINDER NR 2 HAD 798.1 HOURS SINCE NEW. CYLINDER NR 4 HAD 897.8 HOURS SINCE NEW.  TOTAL TIME ON ENGINE IS 1504.2 HOURS SINCE OVERHAUL. ALL CYLINDERS WHERE INSTALLED NEW AT OVRHAUL. CYLINDER NR 4 WAS REPLACED AT 606.4 HRS DUE TO CRACKED CYLINDER HEAD. AT 706.0 HRS CYLINDERS 1,2,3,5,6 WHERE ALL REPLACED DUE CRACKED CYLINDER HEADS DETECTED IN CYLINDER ASSY NR 2,3, AND 6 (TC NR 20060514002)                                                                                                                                                                                                                                 1H71 3O3  O  A4CE    E5CE    5  CP36EA    
20060719000442006071900044SO  2006       7          19         CA060514003      220060429G8530TIST712ACA      CYLINDER HEAD                           CESSNA206   U206G       2073356CE  CONT  O520  IO520F      17032SO  HARTZLHCJ3Y PHCJ3YF1    GL  ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       884  884                           572522                      (CAN) DURING 200 HR INSPECTION CYLINDERS 1,2, AND 5 WHERE FOUND TO BE CRACKED IN THE CYLINDER HEAD CRACKS WHERE DETECTED VISUALLY AND WITH THE AID OF CYLINDER LEAKAGE CHECK AND SOAP WATER SOLUTION.  (TC 20060514003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1H71 3O3  O  A4CE    E5CE    5  CP36EA    
20060719000452006071900045SO  2006       7          19         CA060514004      220060412G8530TIST712ACA      CYLINDER HEAD                           CESSNA185   A185E       2072818CE  CONT  O520  IO520D      17032SO  MCAULY2A34C D2A34C58    GL  ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       968  968                           282670R                     (CAN) CYLINDERS 3, 1, AND 3 REPLACED DUE TO CRACKED CYLINDER HEAD.  ALL CYLINDERS ON THIS ENGINE WHERE REPLACED AT 347.7 HRS SINCE OVERHAUL IAW E.C.I. SB 04-1. (TC NR 20060514004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3O3  O  3A24    E5CE    5  CP3EA     
20060719000462006071900046EA  2006       7          19         CA060514005      120060510G5610NP13932112      WINDSHIELD                              CNDAIRCL600 CL6002C10   1390015EA                                                               COCKPIT         CRACKED         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA       1786                                                           (CAN) RT WINDSHIELD CRACKED ON CLIMBOUT AT 7000 FT,  A/C RETURNED TO BASE. WINDSHIEL WAS REPLACED IAW AMM. THIS WAS A POST SB WINDHIELD. (TC NR 20060514005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F    RTA21EA                        
20060719000472006071900047EA  2006       7          19         CA060515001      120060510G71102285008114      PANEL                                   CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30015NE                              NOSE COWL       MISSING         W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA       22295                                                          (CAN) DURING FLT NR 1 ENG NOSE COWL LWR ACCESS PNL DEPARTED AC (ACCESS PNL). FLIGHT EXPERIENCED A SLIGHT BUFFET DURING FLT. UPON LANDING, FLT CREW DISCOVERED NOSE COWL LWR ACCESS PNL WAS MISSING.  DAMAGE TO TRANSLATING COWL, UPPER NOSE COWL ACCESS PNL, CAUSED BY DEPARTING LWR ACCESS PNL. NR OF LWR ACCESS PNL FASTENERS WERE FOUND STILL ATTACHED MAIN ENG COWLING.  PORTION OF DEPARTED ACCESS PNL WAS FOUND 1500 FT SHORT OF RUNWAY (REMAINDER OF PNL SEC WAS NOT RECOVERED).  NEW LWR COWL ACCESS PNL WAS INSTALLED, DAMAGED TRANSLATING COWLING, UPPER NOSE COWL ACCESS PNL WERE REPLACED.   SHORTS SB (INSP OF COWLING ACCESS PNL FASTENERS ISSUED SEPT/05) IS PRESENTLY BEING CARRIED OUT ON FLEET.                               2L72 4F4  FRTA21EA   E15NE                
20060719000482006071900048EA  2006       7          19         CA060515002      120060503G2810600626401       VENT LINE                               CNDAIRCL600 CL600*             EA  GE    CF34  CF341A           NE                              FUEL            CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       14534                                                          (CAN) MASTER REFUEL PANEL CHECK TO CHECK VALVE FOR OP, FUEL CAME OUT OF LT NACA SCOOP APPROX 2 GALLON, THEN STOP. MAINT WAS ADVISE THIS WAS ONLY HAPPEN WHEN AC WAS PARKED OVERNIGHT. FIGURED THERE WAS A BAD O-RING IN VENT SYS. FUEL WAS DRAINED, FUEL PANELS REMOVED. NOTICED ON VENT LINE, FUEL WAS LEAKING THRU IT. FOUND PIPE HAD A HOLE, CORRODED. PIPE HAD A CAP INTALLED TO THIS VENT LINE, AN UNNAPROVED MOD WAS C/O ON VENT SYS.  SB CAME OUT YEARS EARLIER TO REMOVE DRAIN LINE THAT WAS CONNECTED TO PIPE TO DRAIN ANY FUEL THAT COLLECTED IN VENT SYS BY USE OF EJECTOR PUMP. THIS UNAPPROVED MOD, WATER COLLECTED AT BOTTOM OF PIPE, CORRODED THRU. SB WAS COMPLIED WITH, SYSTEM CHECK SERVICABLE (TC NR 20060515002)            2L72 4F4  FRTA21EA   E15NE                
20060719000492006071900049EA  2006       7          19         CA060515003      120060503G2810600626401       VENT LINE                               CNDAIRCL601 CL6012A12   1900303EA  GE    CF34  CF341A           NE                                              CORRODED        W      K   NONE                                                                                            B  SMOKE/FUMES/ODORS/SPARKS                                                      ININSP/MAINT     1                      CA       14534                                                          (CAN) REFUELLING WAS C/O, MASTER REFUEL PANEL CHECK C/O TO CHECK VALVE FOR OPERATION, WHAT WAS NOTICED, FUEL CAME OUT OUT OF THE LT NACA SCOOP APPROXIMATE 2 GALLON, THEN STOP. MAINT WAS ADVISED,THIS WAS ONLY HAPPENING WHEN A/C WAS PARK OVERNIGHT. SO MAINT CREW FIGURED THAT THERE WAS A BAD O-RING IN VENT SYS. A/C RETURED TO MAINT, FUEL WAS DRAINED AND FUEL PANELS REMOVED, FOUND VENT LINE, FUEL WAS LEAKING THRU IT. PIPE WAS REMOVED, FOUND PIPE HAD A HOLE THRU IT, CORRODED.  PIPE HAD AN A CAP INTALLED TO THIS VENT LINE, A UNAPPROVED MOD WAS C/O ON VENT SYS.   BY DOING THIS UNAPPROVED MOD WATER COLLECTED AT BOTTOM OF PIPE AND CORRODED THRU. S/B WAS COMPLIED WITH AND SYSTEM CHECK SERVICABLE. (TC NR 20060515003)     2L72 4F4  FRTA21AE   E15NE                
20060719000502006071900050SW  2006       7          19         CA060515004      120060508G6410212010750105    BLADE                                   BELL  212   212         1181420SW  PWA   PT6T  PT6T3       52045EA                              TAIL ROTOR      CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       582                                                            (CAN) AT REASSEMBLY OF T/R BLADES IT WAS NOTED THAT WHITE POWDER WAS PRESENT IN THE CUFF AREA OF THE BLADES. BLADES QTY 2 WERE SENT TO COMPOSITE TECHNOLOGY FOR EVALUATION. BOTH BLADES WERE SCRAPPED DUE TO DEEP CORROSION INSIDE OF UPPER AND LOWER GRIP PLATES. TOTAL TIME ON THE BLADES 582.4 HOURS SINCE NEW. (TC NR 20060515004)                                                                                                                                                                                                                                                                                                                                                                                                          1G71 4U4  U  H4SW    E22EA                
20060719000512006071900051CE  2006       7          19         CA060515005      120060501G5511107326022       SPAR                                    CESSNA185   A185F       2072821CE  CONT  O520  IO520D      17032SO  MCAULYD3A34 D3A34C403   GL  HORIZONTAL STAB CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1535                                                           (CAN) 1) SPAR (P/N 0732602-2 2) REINFORCEMENT (P/N 0732603-1 3) BRACKETS (P/N 0732101-4  ALL 3 OF ABOVE ITEMS WERE FOUND CRACKED AND REPLACED.  (TC NR 20060515005).                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H71 3O3  O  3A24    E5CE    5  CP47GL    
20060719000522006071900052NE  2006       7          19         CA060515006      220060514G7321                FCU                                     AMD   FALC10FALCON10    2730101EU  GARRTTTFE731TFE73121C        NE                                              INOPERATIVE     W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             LDLANDING        1                      CA                                                                      (CAN) UPON RIGGING OF FCU, LOW IDLE STOPS ON THE THROTTLE QUADRANT WERE ADJUSTED TO ACHIEVE DESIRED 20 DEGREES ON THE FCU.  THIS ADJUSTMENT WOULD NOT PHYSICALLY ALLOW THE QUADRANT TO DEPLOY THE THRUST REVERSERS.  ENGINES WERE GROUND RUN AND FOUND TO BE SERVICEABLE, ALTHOUGH THRUST REVERSERS WERE NOT CHECKED DURING GROUND RUN.  THE THROTTLE QUADRANT ONLY ALLOWS FOR THE THRUST REVERSERS TO BE DEPLOYED IN ONE POSITION.   NOTE THAT THE ENGINE FCU MUST BE RIGGED AT THE IDLE POSITION ON THE QUADRANT TO ALLOW THE THRUST REVERSER TO BE DEPLOYED AND TO SET THE IDLE POSITION. (TC NR 20060515006)                                                                                                                                2L72 4F4  F  A33EU   E6WE                 
20060719000532006071900053CE  2006       7          19         CA060515007      120060512G2150                BLADE                                   CESSNA500   560CESSNA   2076750CE  PWA   JT15  JT15D5      52112NE                              ACM             BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         CRCRUISE         1                      CA       6800                                                           (CAN) THE PILOTS REPORTED THAT THEY HEARED A HUM COMING FROMTHE A/C SYSTEM. THE ACM WAS INSPECTED AND FOUND ONE COMPRESSOR BLADE BROKEN OFF NEAR THE ROOT AND THE OTHER BLADES HAD LEADING EDGE DAMAGE.  (TC NR 20060515007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F4  FRTA22CE   E25EA                
20060606002282006060600228CE  2006       6          6          CA060516001      120060514G2422100160001       INVERTER                    100160001   RAYTHNDH125 HAWKER800XP 7150012CE  GARRTTTFE731TFE7315BR        WP                              ELECT SYS       FAILED          W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            TOTAKEOFF        1                      CA       791        1350                                                AIRCRAFT DEPARTED AND DURING CLIMB-OUT AN INDICATION OF XS1 BUS FAILURE.  THE CREW COMPLETED THE COCKPIT ABNORMAL CHECK LIST FOR THE ITEM AND RETURNED TO DEPARTURE.  MAINTENANCE WAS ADVISED AND MET THE AIRCRAFT UPON ITS RETURN.  INVESTIGATION FOUND THE ODOR OF BURNT ELECTRICAL UPON OPENING OF THE AFT EQUIPMENT BAY DOOR.  FURTHER INVESTIGATION REVEALED THE NR 1 STATIC INVERTER TO BE FAILED.  AN HOUR HAD ELAPSED SINCE THE AIRCRAFT WAS SHUT DOWN AND THE INVERTER WAS STILL HOT TO THE TOUCH AND THE ODOR OF BURNT ELECTRICAL WAS MOST EVIDENT.  THE INVERTER WAS REPLACED AND THE AC ELECTRICAL SYSTEM WAS FUNCTION TESTED SERVICEABLE.  THE AIRCRAFT WAS RETURNED TO SERVICE.                                                   2L72 4F4  FRTA3EU    E6WE                 
20061018000742006101800074EA  2006       10         18         CA060516002      120060516G32601EN243R1        INDICATOR                               CNDAIRCL215 CL2156B11215       EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  MLG             MALFUNCTIONED   W      O   OTHER                                                                                           N  FALSE WARNING                                                                 APAPPROACH       1                      CA                                                                      (CAN) INDICATOR ON THE LT MAIN LANDING GEAR ALWAYS INDICATES UP AFTER SELECTING DOWN. THE UP LOCK INDICATOR SWITCH HAS BEEN REPLACED. AIRCRAFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2H72 4T4  TRTA14EA   E20NE   6  CP7NE     
20060606002272006060600227CE  2006       6          6          CA060516003      120060515G2752505211984       ACTUATOR                                BEECH 99    99          1154002CE  PWA   PT6   PT6A27      52043EA                              RT OB FLAP      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      ROUTINE VISUAL INSPECTION OF THE FLAP ACTUATORS INDICATED THAT THE OUTBOARD ATTACHMENT FLANGE OF THE RT OUTBOARD FLAP ACTUATOR WAS CRACKED.  THERE WAS NO EVIDENCE OF THE ACTUATOR BEING DROPPED OR OTHERWISE ABUSED.  THE FLANGE WAS BENT SLIGHTLY INBOARD AND THERE WAS EVIDENCE OF THE ACTUATOR CHAFFING ON THE MOUNTING FRAME DURING ITS NORMAL OPERATING CYCLE.                                                                                                                                                                                                                                                                                                                                                                            1L72 3T4  T  A14CE   E4EA                 
20060606002372006060600237CE  2006       6          6          CA060516004      120060513G551007321014        REINFORCEMENT   CESSNA      12320008    CESSNA185   A185F       2072821CE  CONT  O520  IO520D      17032SO                              STABILIZER      CRACKED         W      K   NONE                                                                                            F  FLT CONT AFFECTED                                                             NRNOT REPORTED   1                      CA                                                                      EXCESSIVE MOVEMENT FOUND AT AFT LT HINGE ASSY, INSIDE REINFORCEMENT P/N 0732106-1, ALSO FOUND CRACKED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3O3  O  3A24    E5CE                 
20060606002382006060600238SO  2006       6          6          CA060516005      120060503G7931AS349101        GASKET          LYC         LIO540J2BD  PIPER PA31  PA31350     7103110SO  LYC   O540  TIO540J2BD  41532EA                              ENGINE          DAMAGED         W      K   NONE                                                                                            K  FLUID LOSS                                                                    CRCRUISE         1                      CA                  L217368A                                            WHILE FLYING CRUISE FLIGHT NOTICED ENGINE OIL PRESSURE DROPPING.  SHUT DOWN RT ENGINE AND RETURNED TO BASE.  UPON INVESTIGATION FOUND THAT THE GASKET UNDERNEATH VACUUM PUMP DAMAGED.  VACUUM PUMP CHANGED PRIOR TO FLIGHT.  OIL LEAK NOT DETECTED ON RUN UP.  GASKET P/N AS3491-01 REPLACED.  AIRCRAFT GROUND RUN LEAK CHECKED OK.  NO FURTHER DAMAGE FOUND.                                                                                                                                                                                                                                                                                                                                                                                   1L72 3O3  O  A20SO   E14EA                
20060606002402006060600240NM  2006       6          6          CA060516007      120060513G5610141480149       WINDSCREEN      PPG         141480149   BOEING767   767*               NM  GE    CF6   CF680C2B6F  30025NE                              COCKPIT         FAILED          W      K   NONE                                                                                            O  OTHER                                                                         CRCRUISE         1                      CA                  93026H4349                                          LOCATION APPROX 30 DEGREES WEST AT FL 320 - IAS M .8 AS REPORTED BY THE FLIGHT CREW: WHILE IN CRUISE THE FLIGHT CREW NOTICED A CRACK STARTING IN THE UPPER LEFT CORNER OF THE CAPTAINS FORWARD WINDOW (NR 1) WITH IN A FEW MINUTES THE CRACK HAD SPREAD ALMOST ALL THE WAY TO THE FAR RIGHT.  SHORTLY AFTER THAT THE CREW OBSERVED ARCING OF THE WINDOW HEATER ELEMENT AND LEFT THE WINDOW HEAT IN THE OFF POSITION.  APPROXIMATELY ONE MINUTE LATER THE ENTIRE VIEWING AREA OF THE WINDOW CRAZED.  THE FLIGHT CREW OBSERVED THE CRAZING TO BE THE OUTER PLY AND CONTINUED THE FLIGHT WITHOUT FURTHER INCIDENT.                                                                                                                                 2L72 4F4  FRTA1NM    E13NE                
20060607002362006060700236WP  2006       6          7          CA060516008      120060512G2497                WIRE HARNESS    GENDYN      CV580A      CVAC  440   440         2422902WP  ALLSN 501D  501D13D     03004GL                              ELT WIRING      CHAFED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                  374                                                 DURING INSTALLATION OF  ELT REMOTE SWITCH WIRING, ROUTING OF THE WIRE BEHIND THE FORWARD RT EQUIPMENT SHELF, SEVERAL WIRES WERE FOUND CHAFING INTO THE WIRE BUNDLE THAT RUNS VERTICALLY BEHIND THE SHELF.  THE WIRES WERE CHAFING ON THE BACK EDGE OF THE FLOOR.  THE WIRING WAS REPAIRED AND SECURED AND THE FLOOR WAS TRIMMED TO ENSURE ADEQUATE CLEARANCE.  ALL OTHER AIRCRAFT IN THE FLEET WERE INSPECTED WITH NO OTHER DAMAGE REPORTED.                                                                                                                                                                                                                                                                                                    2L72 4R4  T  6A6     E282                 
20060607002372006060700237SO  2006       6          7          CA060516009      120060424G32306750200         PIN             PIPER       7872322     PIPER PA44  PA44180     7104402SO  LYC   O360  O360*       41514EA                              MLG             CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       4099                                                           DURING LT MLG GEAR REMOVAL A SUBSTANTIAL AMOUNT OF WATER WAS OBSERVED INSIDE MLG RETAINER PIN ASSY.  FURTHER INVESTIGATION REVEALED DEEP PITTING ON INNER SURFACE OF PIN, LOSS OF APPROX 50 PERCENT OF CHROME PLATING ON EXT OF PIN AND ASSY RETENTION BOLT HAD LOST APPROX 35% OF IT'S SHANK DIAMETER NEAR TO IT'S HEAD.  FAILURE OF THIS BOLT WOULD ALLOW RETAINER PIN TO MIGRATE OUT OF POSITION AND RESULT IN MLG COLLAPSE.  THIS DAMAGE BEARS RESEMBLENCE TO A SERVICE DIFFICULTY ALERT AL-2004-06 REPORTED IN 2004.  RT RETAINER PIN ASSY ALSO SHOWED SEVERE CORROSION.  MLG RETAINER PIN ASSEMBLIES WERE REPLACED WITH NEW AND UPON INSTALLATION RETAINER PIN CAVITIES WERE PACKED WITH GREASE TO EXCLUDE WATER FROM THIS AREA.          1L72 3O3  O  A19S0   E286                 
20060607002382006060700238SO  2006       6          7          CA060516010      120060418G32116750200         PIN             PIPER       7872322     PIPER PA44  PA44180     7104402SO                                                               LT MLG          CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3599                                                           DURING LT MLG REMOVAL SEVERE CORROSION WAS OBSERVED ON THE INNER SURFACE OF THE MLG RETAINER PIN.  FURTHER INVESTIGATION REVEALED LOSS OF APPROXIMATELY 50% OF THE OUTER CHROME SURFACE AND THE PIN RETENTION BOLT HAD LOST 20% OF IT'S SHANK DIAMETER NEAR TO THE HEAD.  INSPECTION OF THE RT RETAINER PIN ASSEMBLY ON THIS AIRCRAFT ALSO SHOWED SIMILAR DAMAGE.  FAILURE OF THIS BOLT WOULD ALLOW MIGRATION OF THE RETAINER PIN AND COLLAPSE OF THE MLG ASSEMBLY.  BOTH MLG RETAINER PIN ASSEMBLIES WERE REPLACED WITH NEW AND UPON INSTALLATION THE RETAINER PIN CAVITIES WERE PACKED WITH GREASE TO EXCLUDE WATER FROM THIS AREA.                                                                                                           1L72 3O      A19S0                        
20060607002392006060700239EA  2006       6          7          CA060517002      120060516G612378249047        PCU             HAMSTD      78249047    DHAV  DHC8  DHC8311     1386006EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF15      NE  NR 1 PROP SYS   FAULTY          W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         FR FLT CONT AFFECTED         PARTIAL RPM/PWR LOSS                                CRCRUISE         1                      CA       1753 1753  970834                                              SHORTLY AFTER TAKEOFF, NR 1 PROP WENT SLOWLY IN AND OUT OF FEATHER (GENTLY) THREE TIMES.  PRECAUTIONARY SHUT DOWN OF NR 1 ENGINE CARRIED OUT.  AIRCRAFT DIVERTED TO NEAREST AIRPORT.  MAINTENANCE INSPECTED AND REPLACED NR 1 PROP CONTROL UNIT, GROUND RUN AND LEAK CHECKED SERVICEABLE.  AIRCRAFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                        2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060607002452006060700245NE  2006       6          7          CA060517003      120060505G2720S616561500      DAMPER          SKRSKY      S616561500  SKRSKYS61   S61N        8142104NE  GE    CT58  CT581402    30011NE                              YAW CONT SYS    LEAKING         W      H   DEACTIVATE SYST/CIRCUITS                                                                        KF FLUID LOSS                FLT CONT AFFECTED                                   APAPPROACH       1                      CA       19511256   990281                                              PILOT FELT A YAW ON APPROACH, AND AFTER CONFIRMING A YAW HARDOVER, SWITCHED OFF AUX HYDRAULICS, AND CONTINUED TO LAND.  ON INSPECTION IT WAS FOUND THAT THE PEDAL DAMPER WAS LEAKING EXCESSIVELY DUE TO A BROKEN BOLT AND CAP.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2G72 4U4  U  1H15    1E3                  
20060607002462006060700246WP  2006       6          7          CA060518001      120060512G801072566           RING GEAR       LYC         31M22972    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540*      41532EA                              ENGINE          DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA       572                                                            THE PILOT REPORTED DIFFICULTY STARTING THE AIRCRAFT.  UPON INSPECTION TEETH WERE NOTED TO BE MISSING OFF THE STARTER RING GEAR.  THE ASSEMBLY WAS REPLACED.  THE STARTER DID NOT HAVE ANY DEFECTS ON THE DRIVE GEAR, AND WAS NOT REPLACED.  ROBINSON KNOWS THERE IS A PROBLEM WITH THE STARTER RING GEARS.  THEY HAVE CHANGED THE BRANDS OF STARTERS INSTALLED AT THE FACTORY FROM B&C TO SKYTEC.  THIS AIRCRAFT HAS THE B&C STARTER INSTALLED.                                                                                                                                                                                                                                                                                                 1G71 3O3  O  H11NM   1E4                  
20060626000192006062600019WP  2006       6          26         CA060518002      120060502G801172566           GEAR                                    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              STARTER         DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       634                                                            PILOT REPORTED DIFFICULTY STARTING THE AIRCRAFT.  TEETH WERE FOUND TO BE MISSING FROM THE STATER RING GEAR.  THE STARTER RING GEAR ASSEMBLY WAS REPLACED.  AIRCRAFT TAFT 1187.3.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1G71 3O3  O  H11NM   1E4                  
20060607002472006060700247CE  2006       6          7          CA060518003      120060511G324634A2000204      STRUT                       3450A       CESSNA185   A185F       2072821CE  CONT  O520  IO520D      17032SO                              ATTACH FITTING  SHEARED         W      K   NONE                                                                                            O  OTHER                                                                         LDLANDING        1                      CA       260        34122                                               DURING TOUCH DOWN,  INSTRUCTOR HEARD THE VOICE ADVISORY SYSTEM WITH THE MESSAGE "CHECK GEAR" AND LOST THE LIGHT ON THE BLOCK INDICATOR P/N 2A11179-001 ON THE RIGHT AND SIDE.  DECIDED TO LAND ON LAKE WITH SMALLER WAVE WITH NO PROBLEM.  THE INSTRUCTOR FOUND THE FORWARD STRUT RT P/N 34A2000-204 BROKEN AT THE ATTACHMENT FITTING UPPER FORWARD RT P/N 34A2062-014.                                                                                                                                                                                                                                                                                                                                                                         1H71 3O3  O  3A24    E5CE                 
20060626000202006062600020CE  2006       6          26         CA060518004      120060508G561010138402523     WINDSCREEN                              BEECH 1900  1900C       1154161CE  PWA   PT6   PT6A65B     52043EA  HARTZLHCB4M HCB4MP3     GL  COCKPIT         FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       4401                                                           WINDSCREEN INSIDE PANE SHATTERED IN FLIGHT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4T4  TRTA24CE   E4EA    6  CP56GL    
20060608002872006060800287EA  2006       6          8          CA060519001      120060518G5314NAS110410       BOLT                                    DHAV  DHC8  DHC8311     1386006EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF23      NE  KEELBEAM        MISSING         W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA                                                                      LT AND RT FWD (STN387) KEEL BEAM (STR 31L/31R) TO FRONT SPAR ATTACH BOLTS MISSING (X2).  BOLTS NOT INSTALLED BY MANUFACTURER REF IPC 53-41-00 FIG 10 ITEMS 330, 333 AND 335.  A/C TOTAL TIME 14.0 HRS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060612003292006061200329SO  2006       6          12         CA060519002      220060518G8530TIST712ACA      CYLINDER HEAD                           CESSNA206   U206G       2073356CE  CONT  O520  IO520F      17032SO  HARTZLHCJ3Y PHCJ3YF1    GL  ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1390 1390                          293447R                     CYLINDERS 5 - 6 WERE FOUND TO HAVE CRACKED CYLINDER HEADS DURING A CYLINDER LEAKAGE CHECK.  A SOAP WATER SOLUTION WAS USED TO AID IN LOCATING THE CRACKS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3O3  O  A4CE    E5CE    5  CP36EA    
20060612003312006061200331NM  2006       6          12         CA060519003      120060518G271082740037101     SPRING          DHAV                    DHAV  DHC8  DHC8202     2809007NM                                                               GUST LOCK       BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      1 OF 2 AILERON GUST LOCK SPRINGS FOUND BROKEN WHEN PANELS REMOVED TO PERFORM OTHER MAINTENANCE REF IPC 27-12-00 FIG 20, ITEM 210.  AIRCRAFT TOTAL TIME 19575 HOURS, 12119 CYCLES.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2H72 4T    RTA13NM                        
20060612003332006061200333NE  2006       6          12         CA060521001      220060518G73146272017203      SUPPORT BRACKET                         CNDAIRCL600 CL6002C10   1390015EA  GE    CF34  CF34*            NE                                              BROKEN          W      E   ENGINE SHUTDOWN                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  APAPPROACH       1                      CA                                                                      PRIOR TO FLT, PILOTS CALLED TO HAVE RT SERVICED WITH OIL.  MECHS NOTICED RT HAD BEEN SERVICED SEVERAL TIMES IN RECENT HISTORY. INVESTIGATION FOUND BROKEN BRACKET THAT HOLDS EDP OUTLET HYD LINE TO AGB.  BROKEN BRACKET HAD CHAFED A HOLE IN AGB CASING CAUSING OIL LEAKAGE. ACCORDING TO LOGBOOK IN RDU 3 QTS OIL WAS ADDED TO RT ENG BEFORE FERRY FLT.  NO ENG RUNS BEFORE FERRY TO DESTINATION WHERE IT WAS NOTED, HYD LINE WAS NOT SECURED NOR WAS BRACKET REMOVED.  OIL LVL PER EICAS WAS 14%.  OIL ALL OVER COWLING AND BACK OF ENG.  14% LOW OIL LVL IS CONSISTENT WITH LOW OIL PRESS IN FLT AND QRH PILOT COMMANDED IFSD.  MESA HAVE GE A/C SERV ON SITE TO ROB AN AGB FROM A SPARE ENG AND INSTALL THIS A/C 10104 RT.  INITIAL "ROOT C2L72 4F4  FRTA21EA   E15NE                
20060612003342006061200334EA  2006       6          12         CA060523001      120060522G783022850291109     ARM                                     CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              THRUST REVERSER FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                  NA                                                  DURING AN "R" CHECK, LINE MAINTENANCE FOUND THE LT THRUST REVERSER BLOCKER DOOR AT THE 5 O'CLOCK POSITION TORN OUT.  THE ACTUATING ROD (P/N 228-50291-109) WAS STUCK THROUGH THE DIVERTER FAIRING IPC REF 78-34-01.  AREA INSPECTED FOR POSSIBLE DAMAGE TO FAN CASE, NONE FOUND.  DIVERTER FAIRING (LOWER PORTION) REPLACED.  BLOCKER DOOR AND ACTUATING ROD REPLACED.  LEFT THRUST REVERSER CHECKED SERVICEABLE AND AIRCRAFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                              2L72 4F4  FRTA21EA   E15NE                
20060612003352006061200335NM  2006       6          12         CA060523002      120060519G56105893543129      WINDOW                                  BOEING737   737522      138449FNM  CFMINTCFM56 CFM563C1    13802EU                              COCKPIT         CRACKED         W      B   EMER. DESCENT                                                                                   O  OTHER                                                                         CRCRUISE         1                      CA                                                                      CAPTAINS NR 1 WINDOW SPIDER CRACKED AT 34,000 FT, WINDOW CRACKED THROUGH OUT 50% OF THE WINDOW IN THE OUTER PANE ONLY.  AIRCRAFT FERRIED TO BASE FOR NR 1 WINDOW CHANGE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F4  FRTA16WE   E21EU                
20060612003362006061200336EA  2006       6          12         CA060523003      220060418G7314AF15472         PUMP                                    PIPER PA28  PA28151     7102805SO  LYC   O320  O320E3H     41508EA  SNSNCH74D   74DM        EA  FUEL SYS        FAILED          W      O   OTHER                                                                                           YJ ENGINE STOPPAGE           WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      THIS MECHANICAL FUEL PUMP HAS BEEN INSTALLED NEW.  ENGINE RUN-UP DONE WITHIN PARAMETER WITH FUEL PRESSURE NORMAL AT ALL RPM ON GROUND STATIC RUN-UP.  OWNER RUN-UP BEFORE FLIGHT FOUND FUEL PRESSURE NORMAL.  INFLIGHT IN CRUISE DURING CIRCUIT AT THE AIRPORT ENGINE QUIT AND RESTART AFTER WITH ELECTRIC PUMP ON.  THE FUEL GAUGE PRESSURE SHOWING FULL 10 PSI AND STAY AT 10.  ON GROUND FUEL SYSTEM CHECK WITH GROUND EQUIPMENT TESTER SHOWING RIGHT INDICATING ON AIRCRAFT GAUGE.  PUMP REPLACED WITH NEW LYCOMING PUMP, RUN-UP DONE AND FLIGHT TEST OK.  DEFECTIVE PUMP RETURNED TO ENGINE SHOP.                                                                                                                                          1L71 3O3  O  2A13    E274    5  NP88614   
20060626000352006062600035WP  2006       6          26         CA060523004      120060512G2510C6284           BUCKLE                                  ROBSINR44   R44         7640120WP  LYC   O540  O540F1B5    41532EA                              STRAP           CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) METAL STRAP BETWEEN MOUNTING POINT AND BUCKLE IS CRACKED IN TWO.  TIME ON THIS PART IS UNKNOWN.  TAFT 5902  MFG HAS DEVELOPED A NEW SEAT BELT BUCKLE THAT REPLACES THE STAINLESS STEEL STRAP WITH A FABRIC STRAP. (TC NR 20060523004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1G71 3O3  O  H11NM   E295                 
20060612003382006061200338CE  2006       6          12         CA060523005      120060516G5340NAS57712A       NUT                                     MTSBSIMU2   MU2B36A     5780413CE  GARRTTTPE331TPE3315     01514WP  HARTZLHCB4T HCB4TN5     GL  WING            CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       17439                                                          WHILE CARRYING OUT A WINGS OFF INSPECTION AND COMPLYING WITH SERVICE BULLETIN 103/57-004 WING ATTACHMENT HARDWARE.  INSPECTION, THE RT LOWER FORWARD WING ATTACH BOLT BARRELL NUT WAS FOUND CRACKED THROUGH THE ENTIRE THREADED PORTION OF THE NUT.  THE NUT WAS REPLACED AND TORQUED IN ACCORDANCE WITH THE S/B RECOMMENDATIONS.                                                                                                                                                                                                                                                                                                                                                                                                               1H72 3T4  T  A10SW   E4WE    6  CP40EA    
20060626000362006062600036WP  2006       6          26         CA060523006      120060522G2497C05914          WIRE                                    ROBSINR44   R44RAVENII  7640122WP                                                                               LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       17                                                             (CAN) WHILE INSTALLING OPERATIONAL GEAR INTO A NEW AIRCRAFT, THE MAIN LEAD TO THE BUS BAR ON THE CIRCUIT BREAKER PANEL WAS FOUND LOOSE.  THE HARDWARE DID HAVE A LOCK WASHER.  THIS SAME PROBLEM WAS FOUND ON OTHER AIRCRAFT. (TC NR 20060523006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1G71 3O      H11NM                        
20060626000372006062600037WP  2006       6          26         CA060523007      120060522G2497C05914          WIRE                                    ROBSINR44   R44RAVENII  7640122WP                                                                               LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       17                                                             (CAN) WHILE INSTALLING OPERATIONAL GEAR INTO A NEW AIRCRAFT, THE MAIN LEAD TO THE BUS BAR ON THE CIRCUIT BREAKER PANEL WAS FOUND LOOSE.  THE HARDWARE DID HAVE A LOCK WASHER.  THIS SAME PROBLEM WAS FOUND ON OTHER AIRCRAFT. (TC NR 20060523007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1G71 3O      H11NM                        
20060626000382006062600038WP  2006       6          26         CA060523008      120060522G2497C05914          WIRE                                    ROBSINR44   R44RAVENII  7640122WP                                                                               LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       17                                                             (CAN) WHILE INSTALLING OPERATIONAL GEAR INTO A NEW AIRCRAFT, THE MAIN LEAD TO THE BUS BAR ON THE CIRCUIT BREAKER PANEL WAS FOUND LOOSE.  THE HARDWARE DID HAVE A LOCK WASHER.  THIS SAME PROBLEM WAS FOUND ON OTHER AIRCRAFT. (TC NR 20060523008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1G71 3O      H11NM                        
20060626000392006062600039WP  2006       6          26         CA060523009      120060522G2497C05914          WIRE                                    ROBSINR44   R44RAVENII  7640122WP                                                                               LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       17                                                             (CAN) WHILE INSTALLING OPERATIONAL GEAR INTO A NEW AIRCRAFT, THE MAIN LEAD TO THE BUS BAR ON THE CIRCUIT BREAKER PANEL WAS FOUND LOOSE.  THE HARDWARE DID HAVE A LOCK WASHER.  THIS SAME PROBLEM WAS FOUND ON OTHER AIRCRAFT. (TC NR 20060523009)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1G71 3O      H11NM                        
20060612003402006061200340NM  2006       6          12         CA060523010      120060523G531514A55067        FLOORBEAM                               BOEING737   737724      13844BYNM                                                               BS 986          CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                              F001924                                 FOUND FLOORBEAM AT BS 986 CORRODED AT CLIPNUT HOLES BETWEEN RBL 47 AND RBL 18.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F    RTA16WE                        
20060612003412006061200341NM  2006       6          12         CA060523011      120060523G5315141A550424      FLOORBEAM                               BOEING737   737724      13844BYNM                                                               BS 328          CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                              28786                                   FOUND FWD CABIN AREA FLOORBEAM AT 328 BRL 41 CORRODED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA16WE                        
20060612003422006061200342NM  2006       6          12         CA060523012      120060523G33507002246001      LIGHT                                   BOEING737   737724      13844BYNM                                                               SEAT ROW 14ABC  INOPERATIVE     W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      FOUND SEAT ROW 14ABC RED EMERG EXIT LIGHT DOES NOT ILLUMINATE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F    RTA16WE                        
20060613000462006061300046SW  2006       6          13         CA060524001      120060519G6320212030154101    FITTING                                 BELL  205   205A1       1181414SW  LYC   T53   T5317A      41549NE                                              CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      AIRCRAFT WAS ON SEISMIC DRILL MOVE JOB.  THE ENGINEER WAS DOING HIS DAILY INSPECTION WHEN NOTICED THAT ONE EAR OF THE LIFT LINK FITTING WAS APPEARED CRACKED.  A CLOSER VISUAL LOOK CONFIRMED IT WAS CRACKED.  INVESTIGATING IF  THE BUSHING WAS WRONG FOR THIS INSTALLATION.  THE BELL 205 PARTS MANUAL AND TB 205-91-88 ARE NOT TO CLEAR OF THE DIFFERENT BUSHINGS NEEDED.                                                                                                                                                                                                                                                                                                                                                                    1G71 4U4  U  H1SW    E17EA                
20060613001242006061300124GL  2006       6          13         CA060524002      120060512G3246VALTBS12091     WHEEL                                   DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R98539A     52008NE  HARTZLHCB3R HCB3R304    GL  MLG             CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       804                                                            THIS PART WAS INSTALLED MAY 31/04 IN ACCORDANCE WITH VIKING AIR GROSS WEIGHT INSTRUCTION.  IT WAS NOTICED THAT EARLY CORROSION HAD BEGUN AT THE WHEEL GEAR ATTACHMENT HOLE.  THE CORROSION WAS DEEP AND THE PART WAS REPLACED WITH A NEW UNIT.  POSSIBLE CAUSE FOR THE PREMATURE CORROSION IS WHEN THE STEEL BUSH WAS INSTALLED, REMOVING THE ANNODIZING FROM THE MACHINED HOLE, THAN ALLOWING DISSIMILAR CORROSION TO HAPPEN.                                                                                                                                                                                                                                                                                                                  1H71 3R3  RRCA806    5E1     5  CP28EA    
20060626000402006062600040EU  2006       6          26         CA060524003      120060519G6220350A37122823    YOKE                                    SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1        NE                              M/R HEAD & MAST MISSING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) THE ENGINEER WAS LOOKING AT THE AIRCRAFT AND NOTICED THE THE M/R STATIC STOP YOKE BROKEN OFF AND MISSING OUT OF 3.  THE OTHER STATIC STOPS  WERE INSPECTED AND FOUND ONE CRACKED. THE AC WAS GROUNDED AND APPROPRIATE PARTS WERE ORDERED.  (TC NR 20060524003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1G71 3U3  U  H9EU    E19EU                
20060626000412006062600041SO  2006       6          26         CA060524004      120060521G2822A10014D44       PUMP                                    PIPER PA31  PA31        7103102SO  LYC   O540  TIO540A2C   41532EA  HARTZLHCE3Y HCE3YR2A    GL  FUEL BOOST      FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       1097                                                           (CAN) PILOT REPORTED RT FUEL BOOST PUMP UNSERVICEABLE.  TROUBLESHOOTING FOUND POWER TO THE PUMP.  WHEN THE PUMP WAS CHECKED, THERE WAS NO CONTINUITY THROUGH THE PUMP.  THE REPLACMENT PUMP WAS CHECKED AND FOUND TO HAVE 13 OHMS. (TC NR 20060524004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L72 3O3  O  A20SO   E14EA   5  CP33EA    
20060613001262006061300126SO  2006       6          13         CA060524005      120060514G81204066109020      TURBOCHARGER                            PIPER PA31  PA31        7103102SO  LYC   O540  TIO540A2C   41532EA  HARTZLHCE3Y HCE3YR2A    GL  ENGINE          LEAKING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            872                                                       DURING INSPECTION, OIL WAS FOUND IN BOTH THE COMPRESSOR AND TURBINE SECTIONS OF THE TURBO.  THIS INDICATES THAT THE CENTER SECTIONS OIL SEALS WERE FAILING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L72 3O3  O  A20SO   E14EA   5  CP33EA    
20060613001282006061300128EA  2006       6          13         CA060524006      220060514G7314200F5002        PUMP                                    PIPER PA31  PA31        7103102SO  LYC   O540  TIO540A2C   41532EA  HARTZLHCE3Y HCE3YR2A    GL  FUEL SYSTEM     LOW PRESSURE    W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA            980                                                       DURING GROUND RUN, FUEL PRESSURE OUTPUT FROM THE LEFT ENGINE WAS BELOW NORMAL, AND WOULD FLUCTUATE AT LOWER IDLE SPEEDS.  THE FUEL SERVO SCREEN WAS CHECKED DURING THE INSPECTION AND BITS OF METAL WERE FOUND.  THE PUMP WAS REMOVED AND WHEN THE DRIVE SPLINE WAS ROTATED BY HAND A RESISTANCE TO ROTATION WAS FELT AT A CERTAIN POINT.                                                                                                                                                                                                                                                                                                                                                                                                       1L72 3O3  O  A20SO   E14EA   5  CP33EA    
20060627000852006062700085SW  2006       6          27         CA060524007      120060519G284151509002        CONTROL UNIT                            BELL  212   212         1181420SW  PWA   PT6T  PT6T3       52045EA                              FUEL QTY IND    MALFUNCTIONED   W      O   OTHER                                                                                           L  NO TEST                                                                       CRCRUISE         1                      CA                                                                      (CAN) TROUBLESHOOTING A FUEL QUANTITY INDICATING A/C SYSTEM DEFECT. WITH BOTH POWER SECTIONS RUNNING THE FUEL QUANTITY INDICATION WOULD CHANGE WITH NO FUEL ADDED. FUEL QUANTITY SELECTOR WOULD BE POSITIONED TO LT TANK AND VERY SLOWLY THE INDICATOR WOULD SHOW THE CORRECT QUANTITY. THEN MOVE THE SELECTOR TO RT TANK AND THE FUEL QUANTITY WOULD REACT VERY SLOWLY THE FUEL INDICATOR WOULD READ THE CORRECT QUANTITY. THEN MOVE THE SELECTOR BACK TO THE LEFT TANK AND THE READING WOULD BE DIFFERENT THAN THE ORIGINAL FUEL INDICATION.  WHAT WAS FOUND THE LEFT DC CONTROL UNIT WAS AFFECTING THE A/C FUEL QUANTITY INDICATING SYSTEM. UNIT REPLACED, FUNCTIONAL/ OPERATIONAL TEST, A/C RETURNED TO SERVICE. (TC NR 20060524007)        1G71 4U4  U  H4SW    E22EA                
20060628002192006062800219SW  2006       6          28         CA060524008      120060524G6320214030606005    SPINDLE                                 BELL  214   214B        1182100SW  LYC   T55   T5508D      41555NE                              TRANSMISSION    BROKEN          W      A   UNSCHED LANDING                                                                                 Z  SIGNIFICANT FAILURE REPORT                                                    HOHOVERING       1                      CA            1928  AME52013                                            DONT HAVE ANY OTHER INFO AT THIS TIME, AS THIS INCIDENT JUST OCCURRED THIS MORNING.  WILL ADD INFORMATION AS IT COMES IN.  THIS INCIDENT SEEMS VERY SIMILAR TO ONE 16 OCT 1996 NTSB REPORT NUMBER A96P0231.  WITH ONE GOOD DIFFERENCE, NO LOSS IN FLIGHT CONTROL AND SAFE LANDING.  PART WAS NOTED AND X-RAYED AT TIME OF OVERHAUL.                                                                                                                                                                                                                                                                                                                                                                                                             2G71 4U4  U  H6SW    E4NE                 
20060613001312006061300131NE  2006       6          13         CA060524009      220060520G72509609000408      BEARING                                 SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1        NE                              GAS GEN         FLAKING         W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA       1284       10050TEC                                            WHILE IN CRUISE, THE PILOT HAD AN ENGINE CHIP INDICATION AND RETURNED TO BASE.  THE AME LOOKED AT THE REAR BEARING CHIP DETECTOR AND FOUND METAL ON THE PLUG.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1G71 3U3  U  H9EU    E19EU                
20060613001332006061300133NM  2006       6          13         CA060525001      120060517G561007802           WINDSHIELD                              DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  COCKPIT         CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         DEDESCENT        1                      CA                                                                      UPON DESCENT BETWEEN 8000 FT AND 9000 FT, THE CREW NOTICED SPARKS COMING FROM THE LT WINDSHIELD.  SIMULTANEOUSLY, THE WINDSHIELD DEVELOPED A CRACK.  THE WINDSHIELD HEAT WAS IMMEDIATELY TURNED OFF AND THE AIRCRAFT WAS DEPRESSURIZED.  THE AIRCRAFT LANDED SAFELY 10 MINUTES LATER WITH NO FURTHER INCIDENT.                                                                                                                                                                                                                                                                                                                                                                                                                                  2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060613001342006061300134NM  2006       6          13         CA060525002      120060513G7931                O-RING          JANITROL                DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  OIL COOLER      FAILED          W      A   UNSCHED LANDING                                                                                 J OWARNING INDICATION                                  OTHER                     CLCLIMB          1                      CA            560   L86026903                                           AIRCRAFT DEPARTED NORMALLY AND ON CLIMB-OUT, THE NR 2 OIL PRESSURE ANNUNCIATOR ILLUMINATED BRIEFLY, AIRCRAFT THEN RETURNED TO DEPARTURE AIRPORT.  MAINTENANCE INVESTIGATION REVEALED THAT THE NR 2 OIL COOLER WAS LEAKING OIL AND OIL WAS LEAKING FROM THE VERNATHERM VALVE ASSEMBLY.  THE OIL COOLER WAS REPLACED AND THE VERNATHERM VALVE ASSEMBLY (45E04-1) WAS TRANSFERRED TO THE NEW OIL COOLER WITH NEW O-RINGS (25C85-128/129/130).  GROUND RUNS CARRIED OUT AND NO LEAKS EVIDENT.  AIRCRAFT RETURNED TO SERVICE.  OIL COOLER REMOVED IS OUT FOR REPAIR AT THIS TIME.                                                                                                                                                                    2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060613001382006061300138WP  2006       6          13         CA060525003      220060525G7200                ENGINE                                  BAG   JETSTMJETSTM3212  1500217EU  GARRTTTPE331TPE33110UG  01514WP                              RIGHT           MALFUNCTIONED   W      O   OTHER                                                                                           RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      IN CRUISE, RT ENGINE TORQUE INCREASED TO 104.5%, WHEN TTL TURNED OFF WENT TO 120%.  FUEL FLOW ON RT ENG DROPPED TO 200LBS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4T4  TRTBA15CAA E4WE                 
20060626000422006062600042CE  2006       6          26         CA060525004      120060524G575335165050271     BRACKET                                 BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE  HARTZLHCE4A HCE4A3A     NE  ACTUATOR        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       7347                                                           (CAN) DURING A BASE INSPECTION THE RT OB FLAP ACTUATOR BRACKET WAS FOUND CRACKED. WHEN THE BRACKET WAS REMOVED FROM THE SKIN, IT WAS DISCOVERED THAT THE SKIN WAS ALSO CRACKED. FURTHER INSPECTION REVEALED THAT THE RIB UNBER THE SKIN WAS ALSO DAMAGED. THE FLAP WILL BE REPLACED.  (TC NR  20060525004)                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4T4  TRTA24CE   E26NE   5  CP10NE    
20060613001392006061300139NM  2006       6          13         CA060525005      120060525G5330                SKIN                                    BOEING737   7372Q8C     138448SNM                                                               BS 245          GOUGED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      FOUND SKIN GOUGE AT BS 245 2" INBD OF STR 25L.  REPAIRED IAW CUSTOMER EA.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F      A16WE                        
20060613001412006061300141NM  2006       6          13         CA060525006      120060525G5330                SKIN                                    BOEING737   7372Q8C     138448SNM                                                               BS 1016-1028    DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      EXISTING REPAIR AT BS 1016 AND 1028 FROM STR 15L TO 12L DAMAGED BEYOND LIMITS (DENTED) AND REPAIR IAW CUSTOMER EA.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F      A16WE                        
20060613001432006061300143NM  2006       6          13         CA060525007      120060525G5311                FRAME                                   BOEING737   7372Q8C     138448SNM                                                               BS 490 S24R     CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      FWD PIT DOOR WAY AFT FRAME BS 490 STR 24R CRACKED AND REPAIRED IAW CUSTOMER EA.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F      A16WE                        
20060613001922006061300192EA  2006       6          13         CA060526001      220060525G72503037347         SHROUD                                  BEECH 1900  1900C       1154161CE  PWA   PT6   PT6A65B     52043EA  HARTZLHCB4M HCB4MP3     GL  ENGINE          LOOSE           W      C   ABORTED TAKEOFF                                                                                 MJ OVER TEMP                 WARNING INDICATION                                  TOTAKEOFF        1                      CA       90                                                             DURING TAKEOFF ROLL IT WAS NOTED, RT ENG ITT WAS AT RED LINE AND ENG TQ WAS BELOW REQUIRED T/O VALUE.  T/O WAS ABORTED AND A/C RETURNED TO RAMP.  DURING MX INVESTIGATION, LARGE INCREASES IN ITT READINGS COULD BE SEEN WHEN SELECTING BLEED AIR ON OR ACCELERATING ENG.  ENGINE WAS SPLIT AT THE C FLANGE AND THE CT VANE SHROUD SEGMENTS WERE FOUND TO BE LOOSE AND CONTACTING THE CT DISC BLADES.  PART OF ONE SEGMENT WAS MISSING AND THERE WAS IMPACT DAMAGE NOTED ON THE PT TURBINE WITH METAL IN THE EXHAUST STACKS.  ENGINE IS BEING REPLACED AND SENT FOR INVESTIGATION AND REPAIR TO AN APPROVED ENGINE OVERHAUL FACILITY.  THE ENGINE HAS COMPLETED 90 HOURS SINCE THE LAST HOT SECTION REPAIR.                                     2L72 4T4  TRTA24CE   E4EA    6  CP56GL    
20060613001932006061300193SO  2006       6          13         CA060526002      120060406G8120LW1277885       BYPASS VALVE    GARRTT                  PIPER PA31  PA31        7103102SO  LYC   O540  TIO540A2C   41532EA  HARTZLHCE3Y HCE3YR2A    GL  TURBOCHARGER    CRACKED         W      O   OTHER                                                                                           RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA       3118 3118                                                      RIGHT ENGINE NOT DEVELOPING INCHES OF HG.  AFTER RUN-UP AND ATTEMPTED TO ADJUST DENSITY CONTROLLER, WASTEGATE (VALVE - EXHAUST BYPASS) WAS CHECKED AND BUTTERFLY VALVE FOUND TO BE ROTATING FREELY ON ITS SHAFT.  AFTER REMOVAL OF SAID PART, THE WASTEGATE VALVE WAS INSPECTED AND SHOWED SIGNS OF CORROSION, CRACKING AND CORRODED/SHEARED HOLDING STUD.  ENGINE WAS ON CONDITION, NORMAL OPERATION WAS ACHIEVED AFTER REPLACEMENT OF PART.                                                                                                                                                                                                                                                                                                   1L72 3O3  O  A20SO   E14EA   5  CP33EA    
20060626000432006062600043GL  2006       6          26         CA060526003      220060524G75101885M24601      DUCT                                    BOEING767   767375      1385217NM  GE    CF6   CF680C2*         GL                              11TH STAGE      RUPTURED        W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA       10356497                                                       (CAN) L GEN CONT MSG ILLUMINATED, IN FLIGHT CHECKLIST C/O, L GENERATOR CONTROL REMAINED OFF. ON CLIMB OUT, L OIL PRESS EICAS FLASHED RED NUMBERS DECREASING WENT BLANK - OIL TEMP INCREASING -QRH FOLLOWED ENGINE SHUT DOWN.  FOUND CB FOR LEFT ENGINE OIL PRESSURE TRANSMITTER TRIPPED.  FOUND BLEED DUCT RUPTURED AT A PREVIOUS REPAIR.  THE TRIANGULAR SHAPED HOLE APPROX 2" ALONG EACH SIDE ALLOWED 11TH STAGE AIR FOR THE TURBINE CASE COOLING SYSTEM TO BE DIRECTED ONTO WIRING BUNDLES.  WIRES WERE DAMAGED INCLUDING THOSE FOR THE PERMANET MAGNET GENERATOR AND FOR THE IDG.  WIRE P/NS DAMAGED: W5302-301B-18 W5302-301R-18 W5302-301Y-18 (TC# 20060526003)                                                                           2L72 4F4  FRTA1NM    E23EA                
20060613001952006061300195SO  2006       6          13         CA060526004      220060519G7414M3050           IMPULSE COUPLINGSLICK                   CESSNA206   U206B       2073322CE  CONT  O520  IO520D      17032SO                              MAGNETO         BROKEN          W      D   RETURN TO BLOCK                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA       2157       93120288                                            DURING FLT, PILOT NOTICED A VERY SLIGHT RPM DROP AND SLIGHT ROUGHNESS.  UPON LANDING A GROUND RUN WAS PERFORMED AND WHEN THE IGNITION SWITCH WAS SELECTED TO RT MAG, ENGINE DIED OFF BEFORE SELECTING BACK TO LT OR BOTH.  WHEN COWLS WERE REMOVED IT WAS EVIDENT THAT RT MAG HAD SEPARATED FROM ATTACH FLANGE AND WAS LAYING JUST FWD OF ITS ATTACHMENT POINT.  UPON INSPECTION OF MAG IT APPEARS THAT IMPULSE COUPLING HAD FAILED INTERNALLY AND THROUGH ROTATION AND CENTRIFICAL FORCE HAD WORN AWAY THE CASING OF THE MAG TO THE POINT OF SEPARATION.   MAG WAS REPLACED WITH A NEW UNIT, THE ACCY CASE GEARS WERE VISUALLY INSPECTED, AND THE OIL AND FILTER WERE CHANGED AT THAT TIME AND AGAIN 3 HOURS LATER.                            1H71 3O3  O  A4CE    E5CE                 
20060628002202006062800220    2006       6          28         CA060526005      120060509G63206107435000060   FREEWHEEL UNIT  SKRSKY                                                                                                                  M/R GEARBOX     DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            789                                                       LT P/N 61074-35000-061 S/N C144-00286 RT P/N 61074-35000-060 S/N C144-00279 THESE UNITS WERE CHANGED UPON REQUEST OF THE CUSTOMER AFTER A SUSPECTED FREEWHEEL SLIP.  SEE ATTACHED REPORT AND DIGITAL PICTURES FOR DETAILS.  UNABLE TO ATTACH FILES, WILL E-MAIL THEM.  THESE UNITS HAVE BEEN SENT TO WALDRON AND COMPANY FOR ANALYSIS.                                                                                                                                                                                                                                                                                                                                                                                                                                                    
20060614001262006061400126    2006       6          14         CA060529004      420060428G61228210263C        FLANGE                                  BAG   JETSTMJETSTM3212  1500217EU  GARRTTTPE331TPE33110UG  01514WP  ROTOL R333  R333482F12  GL  PROP GOVERNOR   SPLIT           W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      FOUND OIL DRIPPING UNDER RIGHT ENGINE AFTER SHUT DOWN, ENGINE CLEANED AND CASE NEGATIVE PRESSURE CHECKED, FOUND SERVICEABLE.  ENGINE GROUND RUN/MAX POWER CARRIED OUT.  OIL FOUND TO BE LEAKING FROM THE PROP GOVERNOR.  PROP GOVERNOR REPLACED WITH SERVICEABLE UNIT P/N 8210-263C, S/N 1812067.  GROUND RUN CARRIED OUT SATISFACTORY.                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4T4  TRTBA15CAA E4WE    6  CP61GL    
20060614001992006061400199NE  2006       6          14         CA060529005      220060529G8550493476          O-RING                                  DOUG  DC6   DC6B        3021712WP  PWA   R2800 CB3         52026NE  HAMSTD43E   43E60       NE  NR 4 ENGINE     DISPLACED       W      O   OTHER                                                                                           K  FLUID LOSS                                                                    TXTAXI/GRND HDL  1                      CA            1783                                                      NR 4 ENGINE OUTBOARD UPPER OIL TRANSFER TUBE PLUG FOUND LOOSE AND THE O-RING WAS FOUND DISPLACED, CAUSING RAPID OIL DEPLETION COVERING THE COWLS WITH OIL.  MAINTENANCE STAFF NOTED THIS DEFECT DURING GROUND OPERATION BETWEEN FLIGHTS.  THE PLUG WAS REMOVED AND THE THREADS WERE CHECKED SERVICEABLE.  THE O-RING WAS REPLACED.  THE PLUG WAS INSTALLED AND TORQUED IAW MAINTENANCE MANUAL.  THE ENGINE WAS GROUND RUN, PROP FEATHER OPERATIONAL CHECK COMPLETED.  A LEAK CHECK WAS COMPLETED SERVICEABLE.  A LEAK CHECK WAS ALSO COMPLETED UPON COMPLETION OF FLIGHT AND AIRCRAFT WAS SERVICEABLE.                                                                                                                                          2L74 4R4  R  6A4     E264    6  CP871     
20060614002002006061400200NE  2006       6          14         CA060529006      220060529G8550493476          O-RING                                  DOUG  DC6   DC6B        3021712WP  PWA   R2800 CB3         52026NE  HAMSTD43E   43E60       NE  ENGINE          DISPLACED       W      O   OTHER                                                                                           K  FLUID LOSS                                                                    TXTAXI/GRND HDL  1                      CA            1784                                                      DURING GROUND OPERATION BETWEEN FLIGHTS, MAINTENANCE CREW DISCOVERED OIL ON THE COWL FLAPS.  UPON INVESTIGATION IT WAS DISCOVERED THAT THE UPPER OUTBOARD OIL TRANSFER TUBE PLUG WAS LOOSE.  THE O-RING HAD BECOME DISPLACED.  THE PLUG WAS REMOVED AND THE THREADS WERE INSPECTED AND FOUND SERVICEABLE.  THE O-RING WAS REPLACED.  THE PLUG WAS RE-INSTALLED AND TORQUED IAW MM.  THE ENGINE WAS GROUND RUN, A PROP FEATHER FUNCTION CHECK AND LEAK CHECK WERE ACCOMPLISHED.  ENGINE WAS SERVICEABLE.  THE AIRCRAFT COMPLETED A FLIGHT AND A LEAK CHECK WAS ACCOMPLISHED WITH NO SIGNS OF FURTHER LEAKAGE NOTED.                                                                                                                              2L74 4R4  R  6A4     E264    6  CP871     
20060614002022006061400202GL  2006       6          14         CA060529008      120060524G2820C2P1551A        VENT                                    DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R98539A     52008NE  HARTZLHCB3R HCB3R304    GL  FUEL SYSTEM     WRONG PART      W      K   NONE                                                                                            KB FLUID LOSS                SMOKE/FUMES/ODORS/SPARKS                            ININSP/MAINT     1                      CA       10645                                                          THIS FRONT TANK FUEL VENT TUBE FOUND TO HAVE DISCONNECTED FROM THE RUBBER BLADDER.  THE HOSE CLAMP WAS TIGHT BUT THE TUBE WAS ABLE TO WORK ITSELF FROM THE BLADDER CAUSING FUEL LEAKAGE AND GASES TO ESCAPE FROM THE BLADDER.  IN INVESTIGATING THIS OCCURRENCE IT WAS NOTICED THAT THIS VENT LINE WHICH HAD A DEHAVILLAND P/N DID NOT HAVE A BULK ON THE END, EVEN THOUGH THE DEHAVILLAND DRAWING P/N C2P1551A CLEARLY SHOWS THIS BULBED END.  THIS PART WAS REPLACED WITH A NEW DEHAVILLAND UNIT.                                                                                                                                                                                                                                             1H71 3R3  RRCA806    5E1     5  CP28EA    
20060626000452006062600045CE  2006       6          26         CA060529009      120060518G2913HP3001          PUMP                                    BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA  HARTZLHCB3T HCB3TN3     GL  HYDRAULIC SYS   FAILED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            NRNOT REPORTED   1                      CA                                                                      (CAN) MAINTENANCE INSPECTED THE AIRCRAFT, FOUND MAIN 60A CB TRIPPED  RESET CB AND SYSTEM APPEARED TO FUNCTION NORMAL  FURTHER INVESTIGATION FOUND HYDRAULIC PUMP WOULD INTERMITTENTLY (ONLY OCCUR ON FIRST SYSTEM POWER UP) INTERNALLY BYPASS CAUSING LOW PRESSURE OUTPUT AND PUMP RUN-ON UNTIL CB WOULD TRIP  INVESTIGATION OF THE SYSTEM FOUND WIRE (SPRING MATERIAL) IN FIRST CHECK VALVE OFF PUMP AND MAIN FILTER  HYDRAULIC PUMP REPLACED, SYSTEM FLUSHED AND FUNCTION CHECKED. (TC NR 20060529009)                                                                                                                                                                                                                                        1L72 4T4  T  A24CE   E4EA    6  CP15EA    
20060627002522006062700252CE  2006       6          27         CA060529010      120060521G3241991230512       SERVO                                   CESSNA500   550         2076604CE  PWA   530   PW530A           NE                              BRAKE ANTI-SKID MALFUNCTIONED   W      O   OTHER                                                                                           O  OTHER                                                                         LDLANDING        1                      CA       4017                                                           DURING LANDING, ANTI-SKID INOP ANNUNCIATOR ILLUMINATE THEN EXTINGUISH. ROLLOUT WAS UNEVENTFUL AND DUE LONG RUNWAY, NO BRAKE APPLICATION AT ALL BUT AT END OF RUNWAY RT TURN TO TAXIWAY, BRAKES WERE NON-RESPONSIVE BUT PEDALS WERE EXTREMELY HARD.  MX FOUND PRESS STILL LOCKED IN SYS FROM A/S SERVO "UPSTREAM" SEVERAL HOURS POST INCIDENT.  NO BRAKE PRESS AVAILABLE AT BRAKE UNITS. PWR BRAKE MOTOR NOT CYCLING AS USUAL DUE PRESS LOCK. EVEN WITH ANTI-SKID SWITCHED OFF, BRAKES WOULD NOT RETURN TO MANUAL, MASTER CYLINDER HYD BRAKE SYS AS PER SYS DESIGN.  PRESS DID BLEED OFF HOURS LATER AND SYS RETURNED TO NORM OPS W/O EXT ACTIONS. UNKNOWN WHY TEMP ANTI-SKID LITE DURING LANDING WHICH SEEMS TO HAVE CAUSED ENTIRE BRAKE SYSTEM 1L72 4F4  F  A22CE   E00053EN             
20060627002532006062700253EU  2006       6          27         CA060530001      120060527G63204638001001      TRANSMISSION                            BOLKMS105   BO105S      5626006EU  ALLSN 250C  250C20B     03013GL                              MAIN ROTOR      MAKING METAL    W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      DURING CRUISE, MAIN ROTOR TRANSMISSION METAL PARTICLES LIGHT ILLUMINATE IN COCKPIT.  LAND IMMEDIATELY IN SMALL CLEARING NEAR A ROAD.  IT WAS A SECOND EVENT TO OCCUR WITHIN LAST 10 MINS, BUT FIRST TIME, WARNING LIGHT HAD EXTINGUISHED WHEN PILOT ACTIVATED PULSE CHIP DETECTOR SWITCH.  FOUND A HAIR LIKE PIECE OF METAL, VERY SMALL.  PROBABLY REMAINS OF A .003'' IN OF WIRE USE TO VERIFY OPERATION OF PULSE SYSTEM DURING PREVIOUS SCHEDULE INSPECTION.  THE DETECTOR WAS CLEANED AND REINSTALLED, THE LIGHT REMAIN OFF.  A 20 MINUTES GROUND RUN WAS CARRIED OUT.  WARNING LIGHT REMAIN OFF.  DETECTOR WAS REMOVED, INSPECTED (NO PARTICLE FOUND) AND REINSTALLED.  A/C WAS THEN RETURNED TO SERVICE.                                   1G72 3U3  U  H3EU    E4CE                 
20060626000462006062600046SO  2006       6          26         CA060530003      120060520G2912MS2877816       O-RING                                  PIPER PA31  PA31325     7103105SO  LYC   O540  TIO540F2BD  41532EA  HARTZLHCE3Y HCE3YR2A    GL  HYDRAULIC FILTERFAILED          W      O   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      CA                                                                      (CAN) O-RING IN HYDRAULIC FILTER BOWL BLEW OUT SIDE BETWEEN THE BOWL SEATS. THERE ARE 2 DIFFERENT TYPES SIZES OF O-RING FOR THIS SET UP AS THERE ARE 2 SLIGHTLY DIFFERENT BOWL TYPES. THE O-RINGS ARE THE SAME COLOR AND VERY CLOSE IN SIZE MAKING IT REAL EASY TO PUT THE LARGER O-RING ON THE SMALLER BOWL. THE SMALLER O-RING WILL WORK ON THE LARGER BOWL BUT NOT VISE VERSA. ONCE INSTALLED IT IS IMPOSSIBLE TO TELL WHICH O-RING IS THERE.  (TC NR 20060530003)                                                                                                                                                                                                                                                                           1L72 3O3  O  A20SO   E14EA   5  CP33EA    
20060614002032006061400203CE  2006       6          14         CA060530004      120060512G7160055211313       AIR BOX                                 CESSNA172   172M        2072418CE  LYC   O320  O320E2D     41508EA  MCAULY1C160 1C160DTM    GL  ENGINE          SEPARATED       W      A   UNSCHED LANDING                                                                                 RE PARTIAL RPM/PWR LOSS      VIBRATION/BUFFET                                    DEDESCENT        1                      CA                                                                      STUDENT REMOVED CARB HEAT AFTER EXERCISE AND A/C RPM RESPONDED BY DROPPING, SO CARB HEAT WAS REAPPLIED.  ENG CONTINUED TO GET ROUGHER AND POWER WAS ADDED.  ENDED UP WITH FULL POWER/CARB HOT AND ENGINE RESPONSE WAS 1900 RPM/75 KTS DESCENDING.  ANY CHANGE TO PUT CARB HEAT CAUSED RPM TO DROP SIGNIFICANTLY (BELOW 1500 RPM) LEFT AT POWER FULL/CARB HOT.  ALL ENG INSTRUMENTS READING NORM. A/C WAS NOTICEABLY SHAKING DUE TO ROUGH ENG. ENG RESPONSE STAYED THIS WAY UNTIL ON FINAL, WHERE RESPONSE BECAME NORMAL AND LANDING UNEVENTFUL. UPON EXAM FOUND CARB AIR BOX HAD BEEN REPAIRED PREVIOUSLY, THE PATCH REPAIR RIVETS FAILED, CAUSING REPAIR PATCH TO FALL INSIDE AIR BOX AND PARTIALLY BLOCK CARBURETOR INTAKE. APPLICATION OF CAR1H71 3O3  ONT3A12    E274    5  NP910     
20060614002042006061400204EA  2006       6          14         CA060530005      220060516G853072242           ROCKER COVER                            RKWELL700   700         7630520SW  LYC   O540  TIO540R2AD  41532EA  HARTZLHCE3Y HCE3YR2A    GL  LT ENGINE       SEPARATED       W      A   UNSCHED LANDING                                                                                 YB ENGINE STOPPAGE           SMOKE/FUMES/ODORS/SPARKS                            TOTAKEOFF        1                      CA            314                                                       DURING TAKEOFF, THE CREW NOTED THE LT ENGINE SURGING AND SMOKE FROM THE EXHAUST.  THE AIRCRAFT COMPLETED THE TAKEOFF AND CAME BACK FOR LANDING WITHOUT ANY TROUBLE.  CLOSER INVESTIGATION FOUND THE TAB THAT IS ATTACHED TO THE ROCKER COVER HAD COME OFF.  THIS TAB HOLDS BOTH INTAKE AND EXHAUST ROCKER SHAFTS IN PLACE.  THE EXHAUST ROCKER SHAFT WAS OUT OF PLACE AND THE INTAKE SHAFT HAD COME OUT AND BROKE THE BOSS OFF THE CYLINDER HEAD.  THE ROCKER COVERS ARE MANUFACTURED BY MILLENIUM, THE  ORIGINAL LYCOMING COVERS HAVE THE TAB BONDED ALONG THE ENTIRE MATING SURFACE.  MILLENIUM COVERS HAVE ONLY TWO SMALL SPOT WELDS.  ORDERED ALL NEW CYLINDER COVERS TO REPLACE THESE LIFTER COVERS.                                       1L72 3O3  O  A12SW   E14EA   5  CP33EA    
20060626000472006062600047EA  2006       6          26         CA060530006      220060525G8500                ENGINE                                  CESSNA172   172N        2072434CE  LYC   O320  O320H2AD    41508EA  MCAULY1C160 1C160DTM    GL                  FAILED          W      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      CA                                          RL114176T                   (CAN) ON TAKE-OFF THE AIRCRAFT WOULD NOT DEVELOP FULL POWER SO THE PILOT ABORTED THE TAKE-OFF.  AIRCRAFT WAS BROUGHT INTO THE HANGER AND AME'S REMOVED COWLING AND REMOVED VALVE COVERS. IT WAS NOTED THAT ALL THE CLEARANCES ON THE VALVES WERE TOO LOOSE. AIRCRAFT HAD A NEW ROLLER LIFTERS AND CAM INSTALLED IAW STC SE 03-3 ONLY 24.0 HRS BEFORE BY AN APPROVED ENGINE SHOP. ENGINE SHOP WAS CONTACTED AND THEY CONTACTED OWNER OF STC. OWNER OF THE STC WAS CONTACTED AND THEY REQUESTED THAT THE ENGINE BE SHIPPED TO THEM FOR REPAIR. (TC NR 20060530006)                                                                                                                                                                                1H71 3O3  ONT3A12    E274    5  NP910     
20060627000872006062700087WP  2006       6          27         CA060530007      220060515G72003582681         CARRIER ASSY                            SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP  HARTZLHCE4N HCE4N3      NE  ENGINE          MAKING METAL    W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       328141894                          P54019                      (CAN) OIL SAMPLE RECEIVED FROM WEAR CHECK INDICATING HIGH OIL FILTER WEIGHT W/MAJOR ALUMINUM, MINOR CARBON STEEL IN SAMPLE. ENG REMOVED FOR INSP.  DURING TEARDOWN: PLANETARY CARRIER SPLINE LOCKS STRIPPED/DESTROYED.  CARRIER WORN DUE TO EXCESS PIN LOADING. ALL CARRIER GEARS EXCESS GEAR WEAR.  INSP REVEALED THAT BOLT NR180 IN REDUCTION GEARBOX LOOSENED, CAME IN CONTACT W/ACCESSORY SPUR GEAR CAUSING SPUR GEAR DAMAGE, OIL DETECTOR DAMAGE. MOST COMPONENTS IN REDUCTION GEAR BOX EXIBITED SIGNS OF EXCESS VIBRATION, BOLTS WHICH WERE UNDER TORQUE AS INDICATED BY WEAR PATTERNS ON WASHERS HAD LOOSENED.   PROP INSTALLED ON THIS ENG WAS INSPECTED AND FOUND SERVICEABLE. REASON FOR VIBRATION NOT DETERMINED. (TC NR 20060530007)2L72 4T4  TRTA8SW    E4WE    5  CP10NE    
20060626000482006062600048EA  2006       6          26         CA060530008      220060530G73103027039         LINE                                    BEECH 90    C90A        1152911CE  PWA   PT6   PT6A21      52043EA  HARTZLHCB3T HCB3TN3     GL  FUEL CONTROL    CRACKED         W      ED  ENGINE SHUTDOWN         RETURN TO BLOCK                                                         KRJFLUID LOSS                PARTIAL RPM/PWR LOSS      WARNING INDICATION        TXTAXI/GRND HDL  1                      CA                                                                      (CAN) AIRCRAFT HAD TAXIED TO RUN-UP AREA PRIOR TO TAKEOFF. WHILE COMMENCING ENGINE RUN-UP NOTICED THAT THERE WAS NO THROTTLE RESPONSE ON THE RT ENGINE. CREW CONTACTED MAINTENANCE AND REQUESTED A TOW BACK TO THE HANGER. MAINTENANCE FOUND THAT THE FUEL FEED LINE FROM THE FCU TO THE FUEL FLOW DIVIDER WAS CRACKED AND SPRAYING FUEL INSIDE THE ENGINE NACELLE. CRACK WAS AT THE FCU END OF THE FUEL LINE, CRACK RAN PARALLEL WITH THE SWAGGED FERRULE. FUEL LINE REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20060530008)                                                                                                                                                                                                            1L72 3T4  TRT3A20    E4EA    6  CP15EA    
20060627000882006062700088NM  2006       6          27         CA060530009      120060525G6123JV5             ACTUATOR                                BOMBDRDHC8  DHC8402     1390042NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  AUTOFEATHER SYS INOPERATIVE     W      D   RETURN TO BLOCK                                                                                 O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA                                                                      (CAN) DURING PRE-FLIGHT CHECKS WHEN PROP AUTOFEATHER, ON EITHER ENG, WAS SET TO TEST AND PWR LEVER ADVANCED, PROP WOULD GO INTO TEST (FEATHER) AND STAY THERE, RELEASING TEST SWITCH, SETTING PWR LEVERS TO IDLE DID NOT UN-FEATHER PROP. AUTOFEATHER SELECT SWITCH HAD TO BE SET TO (OFF) FOR SYS TO RETURN TO NORMAL. AUTOFEATHER WOULD ARM NORMALLY WHEN PWR LEVERS WERE ADVANCED TO TAKEOFF PWR, PROBLEM ONLY OCCURRED WHEN SYS WAS SET TO TEST.  SYS WAS DE-ACTIVATED, AC WAS OPERATED UNDER MEL. MAINT FOUND PIECE OF ACTUATOR (JV5) FOR NR 1 PWR CNTRL MICROSWITCH (S13) HAD BROKEN OFF, WAS KEEPING MICOSWITCH (S13) CLOSED ALL THE TIME. MICROSWITCH AND ACTUATOR WERE REPLACED, AUTOFEATHER SYS TESTED NORMAL.                        2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060614002052006061400205NM  2006       6          14         CA060531001      120060530G561058935734        WINDOW                                  BOEING737   737522      138449FNM  CFMINTCFM56 CFM563C1    13802EU                              COCKPIT         FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         APAPPROACH       1                      CA                                                                      ON APPROACH, THE F/O'S NR 4 EYEBROW WINDOW SHATTERED.  APPROACH CONTINUED AND AN UNEVENTFUL LANDING FOLLOWED.  WINDOW REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA16WE   E21EU                
20060614002062006061400206NE  2006       6          14         CA060531003      220060525G8530899353          CYLINDER HEAD                           DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE                              NR 2            CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            1345                                                      CYLINDER ASSEMBLY NR 2 HEAD FOUND CRACKED BETWEEN SPARK PLUG HOLES.  OH ASSEMBLY INSTALLED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1H71 3R3  RRCA806    5E1                  
20060626000492006062600049EA  2006       6          26         CA060531004      220060426G7250                SCOOP                                   BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                              NR 5 BEARING    DETERIORATED    W      C   ABORTED TAKEOFF                                                                                 XJ ENGINE FLAMEOUT           WARNING INDICATION                                  TOTAKEOFF        1                      CA                                                                      (CAN) THE ENGINE FLAMED OUT ON ROTATION RESULTING IN AN ABORTED TAKE-OFF.  SUBSEQUENT INVESTIGATION REVEALED DAMAGE TO THE HPT STUB SHAFT AS A RESULT OF NR 5 BEARING OIL SCOOP DETERIORATION. (TC NR 20060531004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2H72 4T4  TRTA13NM   E00062EN             
20060626000502006062600050EA  2006       6          26         CA060531005      220060407G7321324475520       FUEL CONTROL                            BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA                              ENGINE          INOPERATIVE     W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE THE ENGINE EXPERIENCED AN UNCOMMANDED POWER REDUCTION. THE ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED.  THE FUEL CONTROL WAS SUBSEQUENTLY REPLACED.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20060531005)                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L72 4T4  T  A24CE   E4EA                 
20060627000902006062700090NE  2006       6          27         CA060531007      220060427G7321                SPLINE                                  DHAV  DHC8  DHC8202     2809007NM  PWA   120   PW123D      52152NE                              FUEL CONTROL    WORN            W      E   ENGINE SHUTDOWN                                                                                 R  PARTIAL RPM/PWR LOSS                                                          CRCRUISE         1                      CA       1828       C3106                                               (CAN) ENGINE TORQUE WAS REPORTED TO FLUCTUATE IN CRUISE BY AS MUCH AS 50 PERCENT AND THE ENGINE WAS SHUTDOWN IN FLIGHT.  SUSEQUENT INVESTIGATION REVEALED WORN MECHANICAL FUEL CONTROL DRIVE SPLINES. (TC NR 20060531007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2H72 4T4  TRTA13NM   E20NE                
20060627000912006062700091NE  2006       6          27         CA060531008      220060428G7200                ENGINE                                  AIRTRCAT500 AT502       0390303SW  PWA   PT6   PT6A15AG    52043NE                                              FAILED          W      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  NRNOT REPORTED   1                      CA                                                                      (CAN) THE ENGINE WAS REPORTED TO HAVE LOST POWER IN FLIGHT LEADING TO A FORCED LANDING AND RESULTANT AIRFRAME DAMAGE.  MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060531008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L71 3T4  TNCA9SW    E4EA                 
20060626000512006062600051NE  2006       6          26         CA060531009      220060508G7200                ENGINE                                  BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE                                              MALFUNCTIONED   W      C   ABORTED TAKEOFF                                                                                 YJ ENGINE STOPPAGE           WARNING INDICATION                                  TOTAKEOFF        1                      CA                                          PS0125                      (CAN) DURING TAKE-OFF ROLL THE ENGINE WAS REPORTED TO EMIT A LOUD NOISE ACCOMPANIED BY SEIZURE OF THE POWER SECTION.  SUBSEQUENT INSPECTION REVEALED DAMAGED POWER TURBINE BLADES.  MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060531009)                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4T4  TRTA24CE   E26NE                
20060626000522006062600052SW  2006       6          26         CA060531010      120060404G6200                ROTOR                                   BELL  212   212         1181420SW  PWA   PT6T  PT6T3B      52045NE                              MAIN ROTOR      MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) FOLOWING CLIMB THE MAIN ROTOR SPEED DECREASED UNCOMMANDED AND THE LOW ROTOR RPM WARNING ACTIVATED.  AN EMERGENCY LANDING WAS CARRIED OUT RESULTING IN AIRFRAME DAMAGE.  NR WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR20060531010)                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1G71 4U4  U  H4SW    E22EA                
20060626000532006062600053NE  2006       6          26         CA060531011      220060511G7200                ENGINE                                  PILATSPC7   PC7         7090401EU  PWA   PT6   PT6A25      52043NE                                              POWER LOSS      W      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      CA                                          PF0037                      (CAN) THE ENGINE WAS REPORTED TO HAVE LOST POWER FOLLOWING TAKE-OFF, RESULTING IN A FORCED LANDING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L71 3T3  TRTA50EU   E4EA                 
20060627000922006062700092EA  2006       6          27         CA060531012      220060527G7200                ENGINE                                  BEECH 99    99          1154002CE  PWA   PT6   PT6A28           EA  HARTZLHCB3T HCB3TN3     GL  POWER SECTION   MAKING METAL    W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CRCRUISE         1                      CA            320                           PCE40252                    (CAN) IN CRUISE, THE CHIP LIGHT ACTIVATED ON THE LT ENGINE.  THE ENGINE WAS SHUTDOWN AS A PRECAUTION AND THE AIRCRAFT DIVERTED TO NEAREST FIELD FOR NORMAL LANDING. CFR WAS REQUESTED TO BE ON STANBY.  THERE WAS NO OTHER INDICATIONS OF ENGINE PROBLEMS.  THE CHIP PLUG WAS REMOVED AND CLEANED.  THE OIL SYSTEM WAS FLUSHED AND CHECKED AGAIN FOR CONTAMINATION.  AS A PRECAUTION THE AIRCRAFT WAS FLOWN TO AN ENGINE OVERHAUL FACILITY WHERE THE ENGINE WAS REMOVED.  DETAILS OF THE OVERHAUL FINDINGS WILL BE FORWARDED WHEN AVAILABLE. (TC NR 20060531012)                                                                                                                                                                                1L72 3T4  T  A14CE   E4EA    6  CP15EA    
20060626000542006062600054NE  2006       6          26         CA060531013      220060427G7200                ENGINE                                  BEECH 200   B200        1152922CE  PWA   PT6   PT642A           NE                                              SURGES          W      A   UNSCHED LANDING                                                                                 XJ ENGINE FLAMEOUT           WARNING INDICATION                                  CRCRUISE         1                      CA                                          94609                       (CAN) DURING CRUISE THE ENGINE WAS REPORTED TO SURGE AND SUBSEQUENTLY FLAME OUT.  MFG WILL INVESTIGATE THE EVENT AND WILL ADVISEOF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060531013)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L72 4T4  T  A24CE   E4EA                 
20060627000932006062700093NE  2006       6          27         CA060531014      220060517G7270                PANEL                                   LEAR  60    60LEAR      5170707CE  PWA   305   PW305A      52128NE                              BYPASS DUCT     FRACTURED       W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                          CA0339                      (CAN) DURING GROUND INSPECTION METAL DEBRIS WAS FOUND LODGED IN THE ENGINE BYPASS DUCTING.  THE ENGINE'S INNER BYPASS DUCT PANELS WERE FOUND FRACTURED. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060531014)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F4  FRTA10CE   E35NE                
20060627000952006062700095NE  2006       6          27         CA060531015      220060521G7200                ENGINE                                  BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE                                              MAKING METAL    W      EF  ENGINE SHUTDOWN         ACTIVATE FIRE EXT.                                                      RA PARTIAL RPM/PWR LOSS      FLAME/FIRE                                          DEDESCENT        1                      CA                                          114336                      (CAN) DURING DESCENT THE ENGINE WAS REPORTED TO LOSE POWER ACCOMPANIED BY A FIRE.  THE CREW DEPLOYED FIRE EXTINGUISHERS AND SHUT THE ENGINE DOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED METAL IN THE ENGINE EXHAUST.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4T4  TRTA24CE   E26NE                
20060627001492006062700149NE  2006       6          27         CA060531016      220060530G7250                BLADE                                   BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE  HARTZLHCE4A HCE4A3I     NE  ENGINE          FAILED          W      C   ABORTED TAKEOFF                                                                                 J  WARNING INDICATION                                                            TOTAKEOFF        1                      CA            5771                                                      (CAN) UPON APPLYING TAKEOFF POWER FOR DEPARTURE, THE PILOT HEARD A LOUD BANG. HE THEN INITIATED A SUCCESSFULL REJECTED TAKEOFF.  UPON STOPPING, A PASSENGER CAME FORWARD AND STATED THAT HE THOUGHT SOMETHING FELL OFF THE RT WING.  THE RT ENGINE WAS SECURED. THE AIRCRAFT TAXIED BACK TO THE GATE AND PASSENGERS DISEMBARKED. UPON INVESTIGATION BY MAINTENANCE THE RT ENGINE SEEMS TO HAVE SUFFERED A POWER TURBINE BLADE FAILURE. THE DEBRIS FROM THE BLADES IS WHAT THE PASSENGERS WOULD HAVE SEEN. ENGINE WILL BE FORWARDED TO THE MFG FOR INVESTIGATION. SDR WILL BE LEFT OPEN AND UPDATED WITH INVESTIGATION FINDINGS. (TC NR20060531016)                                                                                              2L72 4T4  TRTA24CE   E26NE   5  CP10NE    
20060627001502006062700150NE  2006       6          27         CA060531017      220060521G7200                ENGINE                                  AEROSPATR42 ATR42*      8680900EU  PWA   120   PW120            NE                                              MALFUNCTIONED   W      E   ENGINE SHUTDOWN                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  APAPPROACH       1                      CA                                          120632                      (CAN) ON APPROACH, ENGINE TORQUE WAS REPORTED TO FLUCTUATE AND THE ENGINE WAS SUBSEQUENTLY SHUTDOWN IN FLIGHT.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2H72 4T4  TRTA53EU   E20NE                
20060627001532006062700153NE  2006       6          27         CA060531018      220060522G7532                BLEED VALVE                             LEAR  60    60LEAR      5170707CE  PWA   305   PW305A      52128NE                              ENGINE          FAILED          W      E   ENGINE SHUTDOWN                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  APAPPROACH       1                      CA                                                                      (CAN) ON APPROACH, THE ENGINE EXPERIENCED COMPRESSOR STALLS ACCOMPANIED BY A RISE IN INTER-TURBINE TEMPERATURE AND ODORS IN THE CABIN.  THE ENGINE WAS SHUTDOWN IN FLIGHT.  THE ENGINE BLEED VALVES AND BLEED VALVE SOLENOID WERE SUBSEQUENTLY REPLACED. (TC NR 20060531018)                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F4  FRTA10CE   E35NE                
20060627001612006062700161NE  2006       6          27         CA060531019      220060522G7320                EEC                                     LEAR  60    60LEAR      5170707CE  PWA   305   PW305A      52128NE                              ENGINE          MALFUNCTIONED   W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB THE ENGINE EEC FAULT LIGHT ACTIVATED FOLLOWED BY A LOUD NOISE AND A LOSS OF POWER.  THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  THE EEC WAS SUBSEQUENTLY REPLACED.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060531019)                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F4  FRTA10CE   E35NE                
20060627001682006062700168EA  2006       6          27         CA060531020      220060515G7200                ENGINE                                  BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A21      52043EA                                              MALFUNCTIONED   W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      CA                                          24774                       (CAN) DURING CLIMB THE ENGINE WAS REPORTED TO EMIT A NOISE AND WAS SHUT DOWN IN FLIGHT.  AN EMERGENCY WAS DECLARED AND THE AIRCRAFT DIVERTED. THE AIRFRAME WAS DAMAGED IN THE SUBSEQUENT LANDING (OVERSHOOT).   MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060531020)                                                                                                                                                                                                                                                                                                                                                                                                                                   1L72 4T4  T  A24CE   E4EA                 
20060627001702006062700170NE  2006       6          27         CA060531021      220060523G7250                TURBINE BLADES                          AEROSPATR72 ATR72212    8680945EU  PWA   PW120 PW127            NE                              TURBINE SECTION FAILED          W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) DURING TAKEOFF CLIMB, THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY AN UNCOMMANDED POWER REDUCTION AND A FIRE WARNING.  THE ENGINE WAS SHUTDOWN IN FLIGHT, AT WHICH POINT THE FIRE WARNING DEACTIVATED. THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060531021)                                                                                                                                                                                                                                                                                                                       2H72 4T4  TRTA53EU   E20NE                
20060627001752006062700175NM  2006       6          27         CA060531022      120060524G793130B296301       SEAL                                    PROPJT200   200A        0140304NM  PWA   306   PW306B           NE                              ACCESSORY GBOX  DAMAGED         W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE, THE ENGINE LOW OIL PRESSSURE WARNING ACTIVATED.  THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INVESTIGATION REVEALED A DAMAGED AND LEAKING ACCESSORY GEARBOX LIP SEAL. (TC NR 20060531022)                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L71 3O4  F  3A18    E35NE                
20060627002542006062700254EA  2006       6          27         CA060531023      220060524G7200                ENGINE                                                                     PWA   PT6   PT6A27      52043EA                                              MAKING METAL    W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA                                          PG0018                      DURING CRUISE, ENGINE OIL PRESSURE WAS REPORTED TO DECREASE ACCOMPANIED BY AN UNCOMMANDED REDUCTION IN POWER.  THE ENGINE WAS SHUT DOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED METALLIC DEBRIS ON THE ENGINE CHIP DETECTOR AND AN INABILITY TO ROTATE.  P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                 4  T          E4EA                 
20060627001842006062700184NE  2006       6          27         CA060531024      220060429G7250                TURBINE BLADES                          BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE                              ENGINE          DAMAGED         W      C   ABORTED TAKEOFF                                                                                 ER VIBRATION/BUFFET          PARTIAL RPM/PWR LOSS                                TOTAKEOFF        1                      CA                                          PS0139                      (CAN) DURING TAKEOFF ROLL, THE ENGINE WAS REPORTED TO VIBRATE ACCOMPANIED BY AN UNCOMMANDED REDUCTION IN POWER.  TAKEOFF WAS ABORTED.  SUBSEQUENT INSPECTION REVEALED DAMAGED POWER TURBINE BLADES. MFG WILL MONITOR INVESTIGATION OF THE EVENT AND REPORT ON ROOT CAUSE ONCE DETERMINED. (TC NR 20060531024)                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4T4  TRTA24CE   E26NE                
20060627001852006062700185SO  2006       6          27         CA060531025      120060531G32214033600         LINK ASSY                               PIPER PA31  PA31350     7103110SO  LYC   O540  TIO540J2BD  41532EA  HARTZLHCE3Y HCE3YR2A    GL  NLG             CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       16119                                                          (CAN) FOUND PART CRACKED ON 1 LUG EXACTLY WHERE NOTED IN PIPER SERVICE LETTER 1088. THIS CRACK WAS VISIBLE WITH THE NAKED EYE, BUT ONLY AFTER THE PAINT WAS REMOVED. (TC NR 20060531025)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L72 3O3  O  A20SO   E14EA   5  CP33EA    
20060627001862006062700186GL  2006       6          27         CA060601001      220060531G7510                GASKET                                  LKHEED382   382G        526414USO  ALLSN 501D  501D22A     03006GL  HAMSTD54H   54H60117    NE  ENGINE          FAILED          W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         JJ WARNING INDICATION        WARNING INDICATION                                  CLCLIMB          1                      CA                                          500934                      (CAN) DEPARTING, CREW OBSERVED A NACELLE OVER HEAT INDICATION ON NR 2 ENGINE. THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT RETURNED TO POINT OF DEPARTURE. ON APPROACH THE LT MAIN GEAR FAILED TO INDICATE DOWN AND LOCKED, AFTER VISUAL CONFIRMATION THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE REPLACED THE GASKET AT THE UPPER MANIFOLD 14TH STAGE BLEED AND THE LT MAIN GEAR DOWNLOCK SWITCH. THE AFFECTED SYSTEMS WERE FUNCTION CHECKED AND THE THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20060601001)                                                                                                                                                                                                                           2H74 4T4  T  A1SO    E282    6  CP906     
20060627001872006062700187EA  2006       6          27         CA060601002      220060531G7220                DUCT                                    BEECH 100   A100        1152915CE  PWA   PT6   PT6A28           EA  HARTZLHCD4N3HCD4N3A     GL  ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) CRACK DEVELOPED IN THE DOMED PORTION OF THE SMALL EXIT DUCT BESIDE THE WELD.  FOUND DURING THE BOROSCOPE INSPECTION. (TC NR 20060601002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L72 3T4  T  A14CE   E4EA    5  CSTC      
20060627001882006062700188NE  2006       6          27         CA060601003      220060527G7261                PACKING                                 PROPJT200   200A        0140304NM  PWA   306   PW306B           NE                              OIL CAP         MISINSTALLED    W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         KJ FLUID LOSS                WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) THE ENGINE LOW OIL PRESSURE WARNING ACTIVATED IN CRUISE AND THE ENGINE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED OIL LOSS ASSOCIATED WITH A MISINSTALLED OIL CAP O-RING PACKING. (TC NR 20060601003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L71 3O4  F  3A18    E35NE                
20060627001892006062700189EU  2006       6          27         CA060601004      120060530G7931                PRESSURE VALVE                          AEROSPATR72 ATR72212A   8680902EU  PWA   PW120 PW127            NE                              OIL SYSTEM      INOPERATIVE     W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) IN TAKE-OFF CLIMB, THE ENGINE LOW OIL PRESSURE WARNING ACTIVATED AND THE ENGINE WAS SHUTDOWN IN FLIGHT.  THE AIRCRAFT RETURNED TO POINT OF DEPARTURE.  THE ENGINE OIL PRESSURE REGULATING VALVE WAS REPLACED. (TC NR 20060601004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2H72 4T4  TRTA53EU   E20NE                
20060627001902006062700190NE  2006       6          27         CA060601005      220060531G7250                TURBINE BLADES                          BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE  HARTZLHCE4A HCE4A3I     NE  ENGINE          FRACTURED       W      C   ABORTED TAKEOFF                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  TOTAKEOFF        1                      CA                                          PS0117                      (CAN) DURING TAKE-OFF ROLL THE ENGINE EMITTED A LOUD NOISE AND TAKE-OFF WAS ABORTED.  SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES AND RESULTS, EXHAUST STUB DAMAGE. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060601005)                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4T4  TRTA24CE   E26NE   5  CP10NE    
20060627001912006062700191SW  2006       6          27         CA060601006      120060327G77142090753261      DETECTOR                                BELL  212   212         1181420SW  PWA   PT6T  PT6T3       52045EA                              RPM LIMIT       FAILED          W      K   NONE                                                                                            N  FALSE WARNING                                                                 ININSP/MAINT     1                      CA            83                                                        (CAN) ENGINE OUT LIGHT STAYS ON AFTER ENGINES STARTED. RPM LIGHT INTERMITTENT WITH RPM IN NORMAL OPERATING RANGE.THE RELIABILITY OF THESE UNITS ARE NOT GOOD.IN OUR FLEET OF 4 BELL 212'S WE GO THROUGH 6 RPM BOXES IN 1 SUMMER (TC NR 20060601006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1G71 4U4  U  H4SW    E22EA                
20060627001982006062700198SO  2006       6          27         CA060602002      120060526G214030670000        TUBE                                    PIPER PA23  PA23250     7102308SO  LYC   O540  IO540C4B5   41532EA  HARTZLHCE2Y HCE2YK2     GL  HEATER EXHAUST  SEPARATED       W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING REMOVAL OF A BIRDS NEST IN THE FRESH AIR INTAKE LOCATED IN THE NOSE OF THE AIRCRAFT THE HEATER EXHAUST TUBE WAS FOUND TO BE UNSERVICEABLE.  THE TUBE ITSELF IS A (WOUND) TUBE AND THE WINDINGS NEAR THE ATTACH POINT HAD SEPARATED THAT WOULD ALLOW HOT EXHAUST TO CONTACT THE TUBE SHROUD. (TC NR 20060602002)                                                                                                                                                                                                                                                                                                                                                                                                                    1L72 3O3  O  1A10    1E4     5  CP9EA     
20060627001992006062700199SO  2006       6          27         CA060602003      220060602G7322991026720       THROTTLE CABLE                          CESSNA310   310Q        2074242CE  CONT  O470  IO470VO     17026SO  MCAULY3AF32C3AF32C87    GL  ENGINE          BROKEN          W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) DOING UPPER AIR WORK, IT WAS NOTICED THEIR WAS NO THROTTLE RESPONSE FROM RT ENGINE. THE ENGINE WAS RUNING NORMAL SO THE CREW RETURNED TO AIRPORT AND DID A NORMAL LANDING AND SHUTDOWN OF ENGINE ON TOUCHDOWN. MAINTENANCE FOUND THE THROTTLE CABLE BROKEN AT THE FUEL CONTROL UNIT WHERE THE FLEX CABLE IS CRIMPED INTO THE SOLID ROD. PARTS ON ORDER. (TC NR 20060602003)                                                                                                                                                                                                                                                                                                                                                               1L72 3O3  O  3A10    3E1     5  CP22EA    
20060627002192006062700219SW  2006       6          27         CA060602004      120060529G6220204011179003    DRAG BRACE                              BELL  205   205A1       1181414SW  LYC   T53   T5317A      41549NE                              MAIN ROTOR      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       7778 704                                                       (CAN) THE DRAG BRACE WAS IN THE COMPONENT SHOP GETTING ITS 1200 HR INSPECTION/24 MONTH INSPECTION. THE DRAG BRACE ASSEMBLY WAS PREPARED FOR NDT MAGNETIC PARTICLE INSPECTION. THE NDT SHOP FOUND THIS FITTING WAS CRACKED ON THE IB CURVE. (TC NR 20060602004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1G71 4U4  U  H1SW    E17EA                
20060627002202006062700220EA  2006       6          27         CA060604001      120060522G2460S69381          BUSS BAR                                CNDAIRCL600 CL6002C10   1390015EA  GE    CF34  CF348C1          NE                                              DAMAGED         W      L   ABORTED APPROACH                                                                                J  WARNING INDICATION                                                            APAPPROACH       1                      CA                                                                      (CAN) C/B 1D6 (DC 1 FEED) POPPED ON SHORT FINAL CAUSING VARIOUS SYSTEMS TO GO INOP.  THEY DID A GO AROUND RESETTING THE C/B, IT POPPED AGAIN ON SHORT FINAL. MAINT FOUND THE BUS BAR BETWEEN CBP-D1 AND CBP-1-D7 (IPC 24-08-01, ITEM 275)WAS NOT SECURED DAMAGING THE CIRCUIT BREAKER. MAINT REPLACED THE DAMAGED CIRCUIT BREAKER AND TIGHTENED THE BUS BAR.  OPS GOOD. (TC NR 20060604001)                                                                                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA21EA   EOOO63EN             
20060627002212006062700221EA  2006       6          27         CA060604002      120060525G492038004883        APU                                     CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30015NE                                              INOPERATIVE     W      F   ACTIVATE FIRE EXT.                                                                              AB FLAME/FIRE                SMOKE/FUMES/ODORS/SPARKS                            TXTAXI/GRND HDL  1                      CA                                                                      (CAN) WHILE TAXING IN PREPARATION FOR TAKEOFF, CREW NOTED SMOKE AROUND AC, TOWER REPORTED SMOKE, FLAMES COMING FROM AFT AREA OF AC UNDER NR 2 ENG.  APU WAS SHUTDOWN, CREW THEN ELECTED TO TAXI OFF ACTIVE TAXIWAY TO A NON ACTIVE TAXIWAY. SHORTLY AFTER STOPPING AC, AN APU FIRE MESSAGE WAS POSTED ON EICAS. CREW COMPLETED QRH PROCEDURE FOR APU FIRE. CREW DISCHARGED AT LEAST ONE FIRE BOTTLE, AND FIRE INDICATIONS EXTINGUISHED. CFR RESPONDED AND DISCHARGED HALON INTO APU ENCLOSURE. CREW THEN EVACUATED PASSENGERS THROUGH MAIN CABIN DOOR EXIT USING QRH PROCEDURE. ONE PASSENGER SUSTAINED A CUT FINGER. NO OTHER INJURIES REPORTED.  THE APU WAS REPLACED, AC RETURNED TO SERVICE.                                                2L72 4F4  FRTA21EA   E15NE                
20060627002222006062700222EA  2006       6          27         CA060605001      120060530G3510S694603         LINE                                    CNDAIRCL600 CL6002C10   1390015EA  GE    CF34  CF348C1          NE                              OXYGEN SYS      RUPTURED        W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) PASSING ABOUT 17000 FT ON CLIMBOUT FROM DFW AN QXYGEN LEAK OCURRED FROM OBSERVERS MASK COMPARTMENT AND DEPLETED ALL THE QXYGEN. FOLLOWED OXY LO PRESS PROCEDURE, DECLARED EMERGENCY, DESCENDED AND RETURNED TO DFW.  TROUBLESHOT A/C AND FOUND O2 LINE BEHIND OBSERVERS O2 MASK RUPTURED. REPLACED LINE IAW CRJ MM 35-11-03. INSTALLED SERVICEABLE CREW O2 BOTTLE IAW CRJ MM 35-11-03. NO LEAKS NOTED.   LINE REF TO AIPC 35-13-01 FIG 01-A01 PAGE 2 ITEM 70. (TC NR 20060605001)                                                                                                                                                                                                                                                         2L72 4F4  FRTA21EA   EOOO63EN             
20060627002232006062700223EU  2006       6          27         CA060605002      120060523G6300350A35105901    DISK                                    SNIAS 350   AS350BA     8680817EU  TMECA ARRIELARRIEL1B    6OO30NE                              ROTOR           FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       4734                                                           (CAN) DURING A 500 HOUR INSPECTION, WHILE INSPECTING THE ENGINE TO MGB ASSY IAW MM, WC 63-00-00-601, AME NOTICED BLACK MARKS AROUND 3 OUT OF 6 BOLTS LINKING DISK ASSY TO POWER SHAFT (MARKS LIKE (SMOKING RIVETS). USING A 13MM WRENCH, COULD EASILY ROTATE THOSE 3 BOLTS BY THE HEAD. THE COTTER PINS WERE NORMALLY INSTALLED BUT THE BOLTS HAD LOST THEIR TORQUE. AFTER REMOVAL, BUSINGS OF THE DISK ASSY SHOWED FRETTING MARKS, AND WERE PARTIALLY UNCRIMPED. REPLACED DISK ASSY AND ASSOCIATED HARDWARE PLUS INSPECTIONS ASKED FOR BY WC 63-00-00-601 C/O. (TC NR 20060605002)                                                                                                                                                             1G71 3U3  UNCH9EU    E19EU                
20060627002552006062700255SO  2006       6          27         CA060605003      220060601G8530SA52000A1       CYLINDER HEAD                           CESSNA206   U206F       2073333CE  CONT  O520  IO520F      17032SO                              ENGINE          CRACKED         W      D   RETURN TO BLOCK                                                                                 O  OTHER                                                                         TOTAKEOFF        1                      CA       382                                                            AIRCRAFT HAD JUST TAKEN OFF WHEN THE PILOT HEARD A LOUD BANG, HE TURNED AROUND AND LANDED AGAIN.  UPON INSPECTION OF THE ENGINE, FOUND THE NR 4 CYLINDER WAS CRACKED AT THE HEAD JUST ABOVE THE THREADS WHERE THE HEAD AND CYLINDER ARE JOINED.  CYLINDER WAS REMOVED AND REPLACED.  HAD ENCOUNTERED THE SAME PROBLEM WITH NR 6 AND NR 2 ABOUT 160 HOURS EARLIER HAD TROUBLE WITH NEW PILOTS AND THOUGHT THIS WAS CAUSING PROBLEM.  OVERHAUL WAS CARRIED OUT AT AERO RECIP, THEY WERE CONTACTED AND WILL BE INSTALLING 6 NEW CYLINDERS.                                                                                                                                                                                                         1H71 3O3  O  A4CE    E5CE                 
20060627002242006062700224EA  2006       6          27         CA060605004      120060603G783022850809801     THRUST REVERSER                         CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30015NE                              LEFT            FAILED          W      D   RETURN TO BLOCK                                                                                 J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      CA                                                                      (CAN) FLIGHT CREW REPORTED THAT THEY RECEIVED A  (L REV UNLOCKED) CAUTION MESSAGE ON RUNWAY AND LINED UP FOR TAKEOFF WITH NO REPORTED CHANGE TO THE N1 OR N2 INDICATIONS. MESSAGE THEN FLICKERED ON AND OFF. WHILE TAXIING BACK TO THE GATE THE MESSAGE WENT OUT. AFTER AC SHUTDOWN MESSAGE REAPPEARED. REV LOCKED OUT IAW MEL 78-30-02 AND TASK 78-30-00-040-802. TRACK ASSY NOTED TO BE CRACKED IAW REO 601R-78-30-3253. AC FERRIED, TRACK ASSY REPLACED. AC RELEASED INTO SERVICE. (TC NR 20060605004)                                                                                                                                                                                                                                       2L72 4F4  FRTA21EA   E15NE                
20060627002252006062700225SW  2006       6          27         CA060605005      120060601G3246206020110005    SKID                                    BELL  206   206B        1181511SW  ALLSN 250C  250C20B     03013GL                              MLG             CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       12163                                                          (CAN) DURING A ROUTINE 300 HR INSP OF THE AC, IT WAS NOTED THAT A SMALL PIECE OF PAINT HAD FALLEN OFF OF THE LOWER AFT END OF THE TAIL SKID ASSY, AT THE LOWER WELD BEAD JOINT. UPON FURTHER INVESTIGATION, IT WAS NOTED THAT A SMALL HOLE (APPROX .1875) WAS PRESENT. WHEN THE WELD AREA WAS INSPECTED ON THE OPPOSITE SIDE, A SMALL AREA OF CORROSION WAS ALSO NOTED, BUBBLING UNDER THE PAINT. THE CORROSION WAS REMOVED WHICH REVEALED ANOTHER SMALL HOLE (APPROX .1875). THIS AREA OF THE TAIL SKID ASSY IS ALSO THE LOWEST POINT, WHERE WATER AND CONDENSATION CAN BE TRAPPED. A NEW TAIL SKID ASSY WAS PURCHASED AND INSTALLED ON THE AIRCRAFT. (TC NR 20060605005)                                                                      1G71 3U3  U  H2SW    E4CE                 
20060627002262006062700226SW  2006       6          27         CA060605006      120060531G5320206031121023    WEB                                     BELL  206   206B        1181511SW  ALLSN 250C  250C20B     03013GL                              FUSELAGE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       12163                                                          (CAN) DURING A ROUTINE 300 INSP ON THE AIRFRAME, A CRACK WAS NOTED ON UPPER AFT SECTION OF THE SEAT WEB ASSY. THIS AREA IS PRONE TO STRESS AND CRACKS WHEN THE SEAT PANEL (THAT IS ATTACHED TO IT) IS REMOVED, AND NO SUPPORT IS ADDED TO THE TOP OF THIS WEB ASSY. PEOPLE TEND TO LEAN OVER THIS AREA, PUTTING THEIR HANDS ON THE TOP OF THE WEB AND THE WEB ENDS UP SUPPORTED THE PERSONS WEIGHT. THIS IS THE PROBABLE CAUSE OF THE CRACK, WHICH CAN HAPPEN OVER TIME. THE WEB ASSY WAS REPLACED WITH A NEW PIECE, AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060605006)                                                                                                                                                              1G71 3U3  U  H2SW    E4CE                 
20060627002272006062700227GL  2006       6          27         CA060605007      220060603G72107636109103104   SHAFT                                   SKRSKYS76   S76A        8143006NE  ALLSN 250C  250C30S     03013GL                              ENGINE          BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) THREADED END BROKEN OFF DURING ASSY.  (ENGINE POWER OUTPUT ADAPTOR SHAFT) (TC NR 20060605007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1G72 3U3  U  H1NE    E1GL                 
20060627002282006062700228SW  2006       6          27         CA060605008      120060531G5313206031123059    LONGERON                                BELL  206   206B        1181511SW  ALLSN 250C  250C20B     03013GL                              FUSELAGE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       12163                                                          (CAN) DURING A ROUTINE 300 HR INSP, A CRACK WAS FOUND ON THE LONGERON ABOVE THE LT REAR PASSENGER DOOR, AT THE FWD ATTACHMENT TO THE ROLLOVER BULKHEAD. THE CRACK ORIGINATED AT THE ATTACHING RIVETS. THE LONGERON WAS REPLACED WITH A NEW PIECE, AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060605008)                                                                                                                                                                                                                                                                                                                                                                                                                                 1G71 3U3  U  H2SW    E4CE                 
20060627002292006062700229EU  2006       6          27         CA060605009      120060603G2497                WIRE                                    AEROSPATR42 ATR42300    8680920EU  PWA   120   PW120            NE  HAMSTD14SF  14SF5       NE  AC GEN          CHAFED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) WE HAD BEEN HAVING TROUBLES WITH NR 2 AC GENERATOR FAULTS IN FLIGHT. AFTER READING SDR NR 20050427005, WE CHECKED OUR ATR AND DISCOVERED NR 2 AC GEN WIRING CHAFING AND ARCING ON NR 2 STARTER GENERATOR COOLING DUCT. WIRING REPAIRED AND INSULATED AS REQUIRED. WIRING SECURED TO PREVENT FUTURE CHAFING. (TC NR 20060605009)                                                                                                                                                                                                                                                                                                                                                                                                           2H72 4T4  TRTA53EU   E20NE   6  CP7NE     
20060627002302006062700230SW  2006       6          27         CA060605010      120060513G6320204040009061    TRANSMISSION                            BELL  204   204B        1181404SW  LYC   T53   T5313B      41549NE                              MAIN ROTOR      MAKING METAL    W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) METAL PARTICLES FOUND IN TRANSMISSION INTERNAL FILTER AFTER ROUTINE INSPECTION.  NO CHIP LIGHT INDICATION. OIL DRAINED WITH NEW FILTER INSTALLED, AIRCRAFT RUN FOR ONE HOUR ON GROUND WITH METAL PARTICLES FOUND IN INTERNAL AND INLINE FILTER ASSY.  NO CHIP LIGHT INDICATION. TRANSMISSION WAS REMOVED WITH T.S.N. 6631.1 T.S.O. 472.3 (TC NR 20060605010)                                                                                                                                                                                                                                                                                                                                                                              1G71 4U4  U  H1SW    E17EA                
20060627002312006062700231NE  2006       6          27         CA060605011      220060529G7323430110116       GOVERNOR                                SNIAS 350   AS350D      8680803EU  LYC   LTS101LTS101600A2 41560NE                              MAIN ROTOR      MALFUNCTIONED   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            2334                                                      (CAN) HELICOPTER STARTED NORMALLY BUT WHEN THE THROTTLE WAS ADVANCED TO THE GATE (100 PERCENT NR), THE MAIN ROTOR STARTED OVERSPEEDING (400 RPM APPROX). THE THROTTLE WAS THEN PULLED BACK AND THE ROTOR SPEED DROPPED. WHEN THE THROTTLE WAS ADVANCED INTO THE GATE AGAIN, THE NR STARTED OSCILLATING BETWEEN 360 AND 400 NR WITH NO INPUT FROM THE THROTTLE OR COLLECTIVE. THE GOVERNOR WAS REPLACED AND THE PROBLEM WENT AWAY. (TC NR 20060605011)                                                                                                                                                                                                                                                                                           1G71 3U3  U  H9EU    E5NE                 
20060627002322006062700232SW  2006       6          27         CA060605012      120060525G6210212015501115    BLADE                                   BELL  212   212         1181420SW  PWA   PT6T  PT6T3       52045EA                              MAIN ROTOR      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3417                                                           (CAN) MAIN ROTOR BLADE SMALL DEBOND FOUND ON LOWER SURFACE APPROX 81.5 INCHES FROM BUTT END JUST AFT OF THE STAINLESS STEEL LEADING EDGE STRIP ON DISASSEMBLY. (APRIL 07 2006) BLADE WILL BE INSPECTED WHEN ARRIVING BACK FOR REPAIR EVALUATION. PAINT REMOVED FROM DEBOND AREA WITH A SMALL CRACK FOUND CHORD WISE APPROX .7500 OF AN INCH LONG.(MAY 25 2006)  (TC NR 20060605012)                                                                                                                                                                                                                                                                                                                                                             1G71 4U4  U  H4SW    E22EA                
20060627002332006062700233WP  2006       6          27         CA060606001      120060605G6240B3203           WARNING HORN                            ROBSINR44   R44RAVENII  7640122WP                                                               COCKPIT         INTERMITTENT    W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       17                                                             (CAN) WARNING HORN WOULD NOT BE TRIGGERED BY THE COLLECTIVE MICRO SWITCHES.  THE UNIT WOULD ONLY CLICK WHEN ACTIVATED AND TAPPING DIRECTLY ON THE UNIT WOULD THEN TRIGGER THE HORN.  WIRING WAS CORRECT, AND NOT PART OF THE SNAG. (TC NR 20060606001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1G71 3O      H11NM                        
20060627002342006062700234WP  2006       6          27         CA060606002      120060512G6240B3203           WARNING HORN                            ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                                              FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       31                                                             (CAN) LOW ROTOR RPM WARNING HORN NOT SOUNDING.  REPLACED WITH A SERVICEABLE UNIT, NO FURTHER FAULTS FOUND. (TC NR 20060606002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1G71 3O3  O  H11NM   1E4                  
20060627002352006062700235SW  2006       6          27         CA060606004      120060605G324020700600        LINE            CLEVELAND   3098C       AIRTRCAT500 AT502B      0390307SW  PWA   PT6   PT6A34AG    52053NE  HARTZLHCB3T HCB3TN3     GL  BRAKE ASSY      CRACKED         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       1910                                                           (CAN) PILOT REPORTED RT BRAKE ALWAYS GOES SOFT WHILE TAXING. AFTER INSPECTING ENTIRE BRAKE INSTALLATION FOR LEAKS,  FOUND THE FWD AND AFT BRAKE CALIPER INTERCONNECT HOSE, FWD FITTING CRACKED. THIS CRACK WAS ONLY APPARENT WHEN THE BRAKES HEAT UP AND THE CRACK OPENED AS IT EXPANDED, CAUSE FLUID TO LEAK. THE HOSE WAS REPLACED WITH NEW UNIT AND BRAKES BLED WITH NO FURTHER FAULTS. (TC NR 20060606004)                                                                                                                                                                                                                                                                                                                                  1L71 3T4  TNCA17SW   E4EA    6  CP15EA    
20060627002362006062700236WP  2006       6          27         CA060606005      120060512G7720624600718       GAUGE                                   ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              CYLINDER HEAD   STICKING        W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       31                                                             (CAN) CHT WAS REPORTED TO BE STICKING.  THE GAUGE WAS FOUND TO BE NOT INSTALLED PROPERLY, CAUSING THE NEEDLE TO RUB ON THE FACE.  THE GAUGE WAS REINSTALLED, AND NO FURTHER FAULTS WERE FOUND. (TC NR 20060606005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1G71 3O3  O  H11NM   1E4                  
20060627002372006062700237NE  2006       6          27         CA060606006      220060605G7310                FILTER                                  AEROSPATR42 ATR42300    8680920EU  PWA   120   PW120            NE  HAMSTD14SF  14SF5       NE  FUEL SYS        CLOGGED         W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) IN CRUISE FLIGHT CREW NOTICED NR 1 ENGINE FUEL FILTER CLOG LIGHT ON. AIRCRAFT RETURNED TO BASE. MAINTENANCE REMOVED NR 1 ENGINE LP AND HP FUEL FILTERS FOR INSPECTION. LARGE AMOUNTS OF CONTAMINENTS FOUND IN LP. FILTERS WERE REPLACED. GROUND RUN CARRIED OUT. THIS IS THE SECOND OCCURANCE OF FUEL CLOG WARNING. 1ST AFTER 25 HRS FOLLOWING C-CHECK INSP. THE SECOND 1000HRS FOLLOWING C-CHECK. (TC NR 20060606006)                                                                                                                                                                                                                                                                                                                    2H72 4T4  TRTA53EU   E20NE   6  CP7NE     
20060627002382006062700238EA  2006       6          27         CA060606007      120060602G2913848847          PUSH-PULL CABLE BOMBDR      848847      CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              HYDRAULIC PUMP  FAILED          W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA       5103 5103  MX564379                                            (CAN) DURING CLIMB CREW RECEIVED NR 3 HYDRAULIC HIGH TEMPERATURE CAUTION LIGHT. CREW ELECTED TO RETURN TO ORIGINATING AIRPORT.  MAINTENANCE REPLACED NR 3 B HYDRAULIC PUMP.  A/C RETURNED TO SERVICE. (TC NR 20060606007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F4  FRTA21EA   E15NE                
20060627002392006062700239CE  2006       6          27         CA060606008      120060527G5697MS24166D1       RELAY                                   BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE  HARTZLHCE4A HCE4A3A     NE  LOW HEAT        DAMAGED         W      H   DEACTIVATE SYST/CIRCUITS                                                                        L  NO TEST                                                                       NRNOT REPORTED   1                      CA                                                                      (CAN) WHEN GROUND POWER WAS APPLIED TO THE AIRCRAFT IT WAS NOTICED THAT THE LT HEATED WINDSHIELD WAS WARM AND ANTI-ICE SWITCH WAS OFF. POWER TO WINDSHIELD, LIMITER IN LT NACELLE, WAS PULLED. INSP OF THE LT WINDSHIELD ANTI-ICE HI/LO RELAYS, BEHIND INSTRUMENT PANEL, REVEALED THAT TERMINAL A2 OF LO HEAT RELAY HAD HEAT DAMAGE AND WAS NO LONGER ATTACHED TO RELAY, IT WAS STILL ATTACHED TO WIRE H16A8, WIRE WAS NO LONGER ATTACHED TO RELAY AND ABOUT ONE INCH OF THE INSULATION FROM WIRE END WAS MISSING. RELAY INTERNAL CONTACTS A1 TO A2 SHOW EXCESSIVE PITTING AND ARCING. RELAY MS24166-D1 WAS REPLACED AND WIRE H16A8 WAS ALSO REPLACED.  (TC NR  20060606008)                                                                    2L72 4T4  TRTA24CE   E26NE   5  CP10NE    
20060627002402006062700240GL  2006       6          27         CA060606009      220060529G7322412B0220        CONTROL CABLE                           BELL  206   206B        1181511SW  ALLSN 250C  250C20B     03013GL                              THROTTLE        BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       7112                                                           (CAN) CABLE BROKE APPROXIMATELY 9.5 FROM END. (TC NR 20060606009)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1G71 3U3  U  H2SW    E4CE                 
20060627002412006062700241CE  2006       6          27         CA060606010      120060603G2910GPP125040       PRESSURE SWITCH                         CESSNA208   208         2073702CE                                                               HYD SYSTEM      FAILED          W      L   ABORTED APPROACH                                                                                O  OTHER                                                                         APAPPROACH       1                      CA       38                                                             (CAN) UPON APPROACH FOR LANDING, WHEELGEAR WOULD NOT EXTEND (AMPHIBIAN AIRCRAFT) ABORTED APPROACH , AICRAFT LANDED ON FLOATS AT WATER BASE. AIRCRAFT PLACARDED (FLOATPLANE OPERATION ONLY). (TC# 20060606010)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3T    NTA37CE                        
20060627002422006062700242EA  2006       6          27         CA060606011      220060605G7261130F0014S0314   LINE                                    BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA                              OIL             LEAKING         W      C   ABORTED TAKEOFF                                                                                 KBJFLUID LOSS                SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION        TOTAKEOFF        1                      CA                                                                      (CAN) WHILE APPLYING TAKEOFF POWER THE PILOTS NOTICED SMOKE IN THE CABIN AND ABORTED THE TAKEOFF WITHOUT INCIDENT. DURING INVESTIGATION MAINTENANCE DISCOVERVED THAT A RECENTLY REPLACED OIL PRESSURE LINE TO THE TORQUE TRANSMITTER MANIFOLD WAS LEAKING AT THE FLARE FITTING. THE HOSE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20060606011)                                                                                                                                                                                                                                                                                                                                                                                 1L72 4T4  T  A24CE   E4EA                 
20060627002432006062700243SW  2006       6          27         CA060606012      120060530G3246                BEARING                                 SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE33111U   01514WP  MCAULY4HFR344HFR34C652  NE  LT MAIN WHEEL   FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) MAINT WAS ADVISED BY BASE AT DEPARTURE THAT LT IB MAIN WHEEL ASSY HAD FALLEN OFF AC ON TAKEOFF.  AC CONTINUED TO MAINT BASE WHERE IT DID FLY BY TO DETERMINE IF WHEEL WAS MISSING.  IT WAS DETERMINED THAT WHEEL ASSY WAS NOT ON THE AC.  AC LANDED WITHOUT INCIDENT.  LWR GEAR ASSY WAS REMOVED AND REPLACED WITH SERVICEABLE LWR GEAR, WHEEL ASSEMBLIES INCLUDING BRAKES.  AC RETURNED TO SERVICE.  UPON INVESTIGATION OF LWR GEAR IT WAS DISCOVERED THAT OUTER WHEEL BRG WAS HEAT DISCOLORED,  OUTER RACE AND CAGE WERE MISSING.  INNER RACE SHOWED NO SIGNS OF HEAT DISCOLORATION, CAGE WAS STILL ON THE INNER RACE ALTHOUGH QUITE DAMAGED.  FOR AN UNDETERMINED REASON OUTER RACE FAILED AND CAUSED ALL DAMAGE.  (TC NR 20060606012) 2L72 4T4  TRTA8SW    E4WE    6  C3PNE     
20060627002442006062700244NE  2006       6          27         CA060607001      220060523G7200                ROTOR                                   CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              LT ENGINE N2    SEIZED          W      A   UNSCHED LANDING                                                                                 EYJVIBRATION/BUFFET          ENGINE STOPPAGE           WARNING INDICATION        CLCLIMB          1                      CA                                                                      (CAN) AS THE AIRCRAFT WAS CLIMBING, FLIGHT CREW HEARD A LOUD BANG AND LOST THE LT ENGINE.  THEY NOTICED THAT THE ITT WAS AT 998 DEGREES AND AN ENGINE (VIB) ON THE N2 GAUGE.  IT WAS FOUND THAT THE LT ENG N2 ROTOR WAS FOUND SEIZED WITH HAVING THE LT ENGINE REPLACED IAW AMM 71-00-00.  ALL ENGINE PERFORMANCE, FUNCTION AND OPERATIONAL CHECKS CARRIED OUT. ALL ENGINE POST GRD RUN LEAK CHECKS CARRIED OUT.  AS FOR NOW, THE PROBLEM IS STILL YET TO BE DETERMINED AND THIS SDR WILL BE UPDATED AS SOON AS THERE IS MORE INFORMATION AVAILABLE.  (TC NR 20060607001)                                                                                                                                                                       2L72 4F4  FRTA21EA   E15NE                
20060627002452006062700245EA  2006       6          27         CA060607002      120060605G321313A04270006     METERING TUBE                           DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A34      52043EA  HARTZLHCB3T HCB3TN3     GL  STRUT           FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         LDLANDING        1                      CA       753                                                            (CAN) FRACTURED AT LOWER THREAD WHERE THE TUBE SCREWS INTO THE PISTON. THIS ALLOWED THE UPPER AND LOWER SECTIONS OF THE SHOCK STRUT TO DISENGAGE CAUSING GEAR COLLAPSE. THE FAILED TUBE IS MADE OF ALUMINUM ALLOY. PART AND PICTURES AVAILABLE UPON REQUEST (TC NR 20060607002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1H72 3T4  TRTA9EA    E4EA    6  CP15EA    
20060627002462006062700246NE  2006       6          27         CA060607003      220060604G7200CF343A1         ENGINE                                  CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30015NE                                              FAILED          W      A   UNSCHED LANDING                                                                                 YJ ENGINE STOPPAGE           WARNING INDICATION                                  CLCLIMB          1                      CA       2194421944                                                     (CAN) DURING CLIMB AT 2000 FT THE NR1 ENGINE FAILED, N1 DROPPED OFF AND TGT PEGGED.  EMERGENCY WAS DECLARED AND AC RETURNED AND LANDED SAFELY. THIS REPORT IS INITIAL ONLY, FURTHER INFORMATION WILL BE FORWARDED ON RECEIPT OF THE TEARDOWN REPORT FROM THE MANUFACTURER. (TC NR 20060607003)                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F4  FRTA21EA   E15NE                
20060803002582006080300258SO  2006       8          3          CA060607004      120060606G2150C180559A        BLOWER                                  EMB   110   EMB110P1    3260122SO  PWA   PT6   PT6A34      52043EA                              VENT            BURNED OUT      W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      NRNOT REPORTED   1                      CA            662                                                       (CAN) SHORTLY AFTER START UP, THE GROUND VENTILATION FAN WAS TURNED ON AND SMOKE STARTED TO ENTER THE AIRCRAFT CABIN. MAINTENANCE FOUND THE GROUND VENT BLOWER TO BE AT FAULT. THE GROUND VENT BLOWER WAS REMOVED AND DEFERRED. THE AIRCRAFT WAS THEN RETURNED TO SERVICE. THE BLOWER WILL BE SENT OUT FOR A STRIP REPORT. (TC# 20060607004)                                                                                                                                                                                                                                                                                                                                                                                                    1L72 4T4  T  A21SO   E4EA                 
20060627002472006062700247EA  2006       6          27         CA060607005      120060520G5610NP13932212      WINDOW                                  CNDAIRCL600 CL6002C10   1390015EA  GE    CF34  CF348C1          NE                              COCKPIT         CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         DEDESCENT        1                      CA       3580                                                           (CAN) DESCENDING THROUGH 11,000 FEET, F/O SIDE WINDOW CRACKED MX REMOVED AND REPLACED SIDE WINDOW IAW CRJ 700 AMM 56-12-01.  W/S HEAT CHECKS GOOD, NO LEAKS NOTED. (TC NR 20060607005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA21EA   EOOO63EN             
20060627002482006062700248EU  2006       6          27         CA060607006      120060607G7930704A37642043    TRANSMITTER                             SNIAS 350   AS350BA     8680817EU  TMECA ARRIELARRIEL1B    6OO30NE                              ENGINE OIL IND  ERRATIC         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       300                                                            (CAN) TRANSMITTER PRODUCED ERRATIC AND ABNORMALLY LOW  OIL PRESSURE INDICATIONS AT ENGINE IDLE SPEED. (TC NR 20060607006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1G71 3U3  UNCH9EU    E19EU                
20060627002562006062700256NM  2006       6          27         CA060608001      120060604G5270                SWITCH                                  BOEING727   727233      138408ANM  PWA   JT8   JT8D15      52051NE                              CARGO DOOR      MALFUNCTIONED   W      O   OTHER                                                                                           N  FALSE WARNING                                                                 CRCRUISE         1                      CA                                                                      AFTER DEPARTURE ON AN ACCEPTANCE FLIGHT AFTER HEAVY MAINTENANCE, THE CREW OBSERVED A NR 1 CARGO DOOR UNSAFE INDICATION.  THE WARNING LIGHT EXTINGUISHED AT 7.2 PSID AFTER REDUCING ALTITUDE TO 11K FT.  THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WHERE THE SWITCH WAS ADJUSTED AND THE AIRCRAFT RELEASED FOR RETURN TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                              2L73 4F4  FRTA3WE    E2EA                 
20060627002572006062700257EA  2006       6          27         CA060608002      220060607G8530LW12416         CYLINDER                                CESSNA172   172P        2072436CE  LYC   O320  O320D2J     41508EA  MCAULY1C160 1C160DTM    GL  NR 2            CRACKED         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       3994 831                           L1487939A                   OIL LEAK FOUND COMING FROM ENGINE COWLING.  AFTER FURTHER INVESTIGATION A CRACK WAS DISCOVERED IN THE NR 2 CYLINDER BARREL.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1H71 3O3  ONT3A12    E274    5  NP910     
             20080520     CE  2008       5          20         CA060608003      120060608G2701041321318       SHAFT                                   CESSNA185   A185E       2072818CE  CONT  O520  IO520D      17032SO  MCAULYD3A34 D3A34C401   GL  AFT END         DAMAGED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       3561                                                           (CAN) ON INSP, IT WAS FOUND THAT THE RT AND LT CONTROL WHEELS WERE LOOSE ON THE CONTROL SHAFTS. AVION RESEARCH STC 00709LA HAD PREVIOUSLY BEEN INSTALLED TO REPLACE THE CONTROL WHEELS, HOWEVER, THE INSTALLATION INSTRUCTIONS CW-8001 REV1 FEB26/98 DO NOT ADDRESS THE DIFFERENCE IN FASTENER SIZES BETWEEN THE ORIGINAL AND REPLACEMENT CONTROL WHEELS. THE STC HOLDER WAS CONTACTED AND A REVISED INSTRUCTION PAGE WAS SUPPLIED THAT REQUIRED ASSEMBLY OF THE CONTROL WHEELS WITH LOCTITE APPLIED TO THE CONTROL SHAFT. NO REVISION DOCUMENT WAS PROVIDED FOR THE ORIGINAL INSTUCTIONS.                                                                                                                                                      1H71 3O3  O  3A24    E5CE    5  CP47GL    
20060627002582006062700258SW  2006       6          27         CA060608004      120060511G5302                BOLT                                    BELL  427   427         1182207SW                                                               TAIL BOOM       LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1606                                                           THE VERTICAL FIN WAS FOUND LOOSE DURING A SCHEDULE INSPECTION.  ONE ATTACHMENT BOLT WAS SHANKED-OUT.  ANOTHER BOLT WAS LOOSE BUT NOT SHANKED.  NO OTHER DAMAGE WAS REPORTED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1G71 3U      R00001RC                     
20060627003342006062700334GL  2006       6          27         CA060608005      220060130G723023064613        IMPELLER        ALLSN                   DOUG  600N  600N        3027377NM  ALLSN 250C  250C47M     03013GL                              COMPRESSOR      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3469       CAC44183                                            (CAN) PILOT REPORTED HIGH TURBINE TEMPERATURES IN FLIGHT, RETURNED TO MAINTENANCE FACILITY AND FOUND CRACK IN COMPRESSOR SCROLL AREA UPON VISUAL INSPECTION AFTER LANDING.  ENGINE ASSY WAS REMOVED AND COMPRESSOR INLET WAS INSPECTED AND FOUND TO HAVE A DAMAGED IMPELLER BLADE.  COMPRESSOR ASSY WAS REMOVED AND SENT FOR FURTHER INSPECTION. IT WAS LATER DETERMINED THE BLADE HAD FAILED FROM A PREVIOUS REPAIR CARRIED OUT TO REMOVE FOD DAMAGE TO THAT BLADE.  SPARE ENGINE WAS INSTALLED AND AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060608005)                                                                                                                                                                                      1G71 3U3  UNCH3WE    E1GL                 
20060627003352006062700335NM  2006       6          27         CA060608006      120060321G5302600N3500505     TAIL BOOM                               DOUG  600N  600N        3027377NM  ALLSN 250C  250C47M     03013GL                                              SEPARATED       W      O   OTHER                                                                                           D  INFLIGHT SEPARATION                                                           NRNOT REPORTED   1                      CA       3615                                                           (CAN) AIRCRAFT INVOLVED IN EXTERNAL LIFT OPERATIONS.  TAIL BOOM ASSY SEPARATED FROM FUSELAGE IN FLIGHT, AIRCRAFT CRASHED ON RT SIDE OF FUSELAGE IN A REMOTE CLEARING. CAUSE OF FAILURE IS UNDER INVESTIGATION. (TC NR 20060608006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1G71 3U3  UNCH3WE    E1GL                 
20060627002592006062700259WP  2006       6          27         CA060608007      120060527G5302                STRUCTURE                               ROBSINR44   R44         7640120WP  LYC   O540  O540F1B5    41532EA                              TAILBOOM        MISMANUFACTURED W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      DURING SCHEDULED MANDATORY REPLACEMENT OF THE HORIZONTAL STABILIZER IT WAS DETERMINED THAT THE NEW PART SUPPLIED BY THE MANUFACTURE WAS INCORECTLY MANUFACTURED.  THE MOUNTING HOLES FOR THE ATTACHMENT OF THE VERTICAL STABILIZERS WERE FOUND TO BE INCORRECTLY LOCATED AND THE ASSOCIATED ANCHOR NUTS WERE MISALIGNED FROM THE HOLES.  PART WAS RETURNED TO THE MANUFACTURE TO DETERMINE THE CAUSE OF THE DEFECT.                                                                                                                                                                                                                                                                                                                             1G71 3O3  O  H11NM   E295                 
20060627002492006062700249NM  2006       6          27         CA060608008      120060606G2622898052          EXTINGUISHER                            BOEING737   737*               NM  CFMINTCFM567CFM567B22   13802NE                              COCKPIT         LEAKING         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       7450                                                           THE A/C WAS AT CRUISE WHEN A HISSING SOUND WAS HEARD.  IT WAS DETERMINED TO BE LEAKAGE FROM THE PORTABLE FIRE EXTINGUISHER IN THE FLIGHT DECK.  THE HISS CHANGED TO A LOUD WHISTLE AS IT INCREASED.  THE CAPTAIN GRABBED THE TOP OF THE EXTINGUISHER AND TWISTED IT AND THE LEAK STOPPED.  THE EXTINGUISHER HAS BEEN RETRIEVED AND IS BEING SENT TO THE VENDOR FOR COMPLETE INVESTIGATION AND ANALYSIS.  ONCE THOSE RESULTS HAVE BEEN RECEIVED THEY WILL BE ADDED TO THIS POSTING.                                                                                                                                                                                                                                                              2L72 4F4  FRTA16WE   E00055EN             
20060627002502006062700250CE  2006       6          27         CA060608009      120060602G561099143809        WINDSHIELD                              CESSNA750   750         2076810CE                                                               COCKPIT         FAILED          W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      CA       2532                                                           AIRCRAFT IN CRUISE AT 41000 FT, SMALL CRACK STARTED AT BOTTOM OB LOWER CORNER.  WITHIN 15 SECONDS THE CRACK EXTENDED ABOUT 3 INCHES THEN WITHIN ABOUT 30 SECONDS THE OUTER PANE SHATTERED.  THE AIRCRAFT WAS FLOWN TO A  AIRPORT AND LANDED WITHOUT INCIDENT.  THE AIRCRAFT WAS FERRIED TO A SERVICE CENTER UNPRESSURIZED AND A NEW WINDSHIELD INSTALLED.                                                                                                                                                                                                                                                                                                                                                                                       2L72 4J    RTT00007WI                     
20060627002512006062700251CE  2006       6          27         CA060608010      120060531G27205565096         CHANNEL                                 CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              RUDDER PEDAL    BROKEN          W      O   OTHER                                                                                           O  OTHER                                                                         LDLANDING        1                      CA       367                                                            PILOTS REPORTED THAT WHEN THE RUDDER PEDALS ARE BOTH PUSHED, THE CO-PILOT'S INSTRUMENT LIGHTS DIM.  INVESTIGATION REVEALED THAT THE PILOT'S RUDDER SUPPORT BRACKET WAS BROKEN AT THE TOP OF THE ATTACH CHANNEL.  THE CO-PILOTS INSTRUMENT LIGHT RHEOSTAT WAS ALSO DAMAGED.  THE SUPPORT CHANNEL AND THE RHEOSTAT WERE BOTH CHANGED.                                                                                                                                                                                                                                                                                                                                                                                                             1L72 4F4  F  A22CE   E1NE                 
20060627003362006062700336NE  2006       6          27         CA060608011      120060518G6320S613520060103   COVER           SKRSKY                  SKRSKYS61   S61L        8142102NE  GE    CT58  CT581401    30011NE                              M/R GEARBOX     CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            233   A14964                                              MAIN GEAR BOX WAS BEING REMOVED FOR INPUT FREEWHEEL REPLACEMENT.  A CRACK WAS DETECTED ON THE RT FOOT OF REAR COVER, AS WELL AS A CRACK ON THE RT REAR AIRFRAME FITTING.  THE  ALIGNMENT FIXTURE WAS USED TO CHECK THE BOX BEAM, AND FOUND TO BE MISALIGNED.  THE RT REAR AND LT FRONT FITTINGS WERE REPLACED TO CORRECT ALIGNMENT, AND GEAR BOX WAS REPAIRED AND REINSTALLED.                                                                                                                                                                                                                                                                                                                                                                  2G72 4U4  U  1H15    1E3                  
20060627003382006062700338EU  2006       6          27         CA060609002      120060406G77121004PGSB        TRANSMITTER                             BRAERO748   HS7482A     4231001EU  RROYCEDART  DART5342         EU  ROTOL R4304 R2124304    EU  TORQUETRANSMTTERFAILED          W      C   ABORTED TAKEOFF                                                                                 J  WARNING INDICATION                                                            TOTAKEOFF        1                      CA                                                                      (CAN) TAKEOFF WAS REJECTED WHEN THE RT ENGINE TORQUE GAUGE BEGAN TO INDICATE ERRATICALLY, MEL 77-02 WAS USED FOR RELIEF AND THE AIRCRAFT CONTINUED ITS TRIP.  MAINTENANCE DETERMINED THAT THE TORQUE TRANSMITTER HAD FAILED. THE TRANSMITTER WAS REPLACED, TESTED SERVICEBLE , MEL CLEARED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20060609002)                                                                                                                                                                                                                                                                                                                                                                                                2L72 3T4  T  A24EU   A196    6  CP899     
20060627003392006062700339NE  2006       6          27         CA060609004      220060607G7510320115          ANTI-ICE VALVE                          BOEING737   737201      1384454NM  PWA   JT8   JT8D9A      52048NE                                              INOPERATIVE     W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      IN CLIMB, THE PORT ENGINE COWL ANTI-ICE LITE ILLUMINATED BRIGHT.  THE AIRCRAFT RETURNED TO BASE.  THE PORT ANTI-ICE VALVE WAS REPLACED, CHECKED SERVICEABLE AND AIRCRAFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  F  A16WE   E2EA                 
20060627003402006062700340EU  2006       6          27         CA060612001      120060606G3230                WIRE HARNESS                            AEROSPATR42 ATR42300    8680920EU  PWA   120   PW120            NE  HAMSTD14SF  14SF5       NE  LT MLG          INOPERATIVE     W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      DURING DEPARTURE, THE LANDING GEAR WOULD NOT RETRACT.  THE AIRCRAFT RETURNED TO POINT OF DEPATURE AND LANDED WITHOUT INCIDENT.  MAINTENANCE REPLACED THE UPPER WIRING HARNESS ON THE LT MAIN LANDING GEAR AND THE AIRCRAFT WAS RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2H72 4T4  TRTA53EU   E20NE   6  CP7NE     
20060705000142006070500014SW  2006       7          5          CA060612003      120060605G5410NAS12918        NUT                                     BELL  430   430         1182150SW                                                               PYLON           CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      ONE (1X) NUT FOUND CRACKED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1G72 3U    RTH9SW                         
20060705000152006070500015SO  2006       7          5          CA060612004      120060609G2910HYC5005         POWERPACK                               PIPER PA28  PA28R200    7102811SO  LYC   O360  IO360C1C    41514EA                              HYD SYS         FAILED          W      A   UNSCHED LANDING                                                                                 FJ FLT CONT AFFECTED         WARNING INDICATION                                  CRCRUISE         1                      CA            902                                                       HYDRAULIC POWER PACK BRUSHES FAILED, PART REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L71 3O3  O  2A13    1E10                 
20060705000162006070500016EA  2006       7          5          CA060612005      120060612G2932215T752322      PRESSURE SWITCH BOMBDR                  CNDAIRCL215 CL2156B11215       EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  ELEVATOR SYS    INTERMITTENT    W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             CRCRUISE         1                      CA       2856                                                           DURING A FLIGHT, HAD 3 SUCCESS IFS INPUTS FROM THE ELEVATOR SYSTEM THEY WERE IN NORMAL MODE AND SUDDENLY ITS WENT TO MANUAL MODE AND BACK TO NORMAL IN A COUPLES OF A FEW SECONDS WITHOUT ANY ACTION FROM THE CREWS .                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2H72 4T4  TRTA14EA   E20NE   6  CP7NE     
20060705000182006070500018EU  2006       7          5          CA060612006      120060610G5100                UNKNOWN                                 SNIAS 350   AS350D      8680803EU  LYC   LTS101LTS101600A2 41560NE                                              UNKNOWN         W      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  APAPPROACH       1                      CA                                                                      ON FINAL APPROACH, APPROX 300 FT AGL, PILOT HEARD LOW ROTOR HORN ACTIVATE AND ENG LOOSE PWR. A SUCCESSFUL AUTOROTATION WAS COMPLETED WITH NO FURTHER INCIDENT.  AFTER LANDING, ENG WAS STILL RUNNING AND ONCE COLLECTIVE WAS LOWERED, ENG RETURNED TO FULL PWR.  PILOT TRIED RAISING COLLECTIVE AND EVERY TIME DID SO, ENG WOULD DECELERATE AND M/R RPM WOULD DECAY UNTIL COLLECTIVE WAS LOWERED AGAIN.  A/C WAS SHUT DOWN AND EXAMINED BY ENGINEER. NO DEFECTS FOUND, AIRCRAFT WAS STARTED AND OPERATED NORM.  PILOT WAS ABLE TO HOVER A/C W/OUT RE-EXPERIENCING PREVIOUS SYMPTOMS.  SYMPTOMS COULD NOT BE DUPLICATED AND CAUSE OF DECEL COULD NOT BE DETERMINED THEREFORE ALL ENG CONTROL COMPONENTS WERE REPLACED BEFORE FURTHER FLT.        1G71 3U3  U  H9EU    E5NE                 
20060627002602006062700260EA  2006       6          27         CA060612007      120060610G3210C6U1180         LEG ASSY                                DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A27      52043EA                              MLG             DAMAGED         W      O   OTHER                                                                                           O  OTHER                                                                         LDLANDING        1                      CA                                                                      DURING A NORMAL LANDING PROCEDURE, THE LEFT MAIN LANDING GEAR BROKE OFF FOR A REASON UNKNOWN TO US.  THE AIRCRAFT CONTINUED TO SKID ON THE STUD OF THE GEAR UNTIL COMING TO A COMPLETE STOP.  AT THE END, THE AIRCRAFT TIPPED TO THE LEFT AND DAMAGED THE LEFT WING TIP.  THERE WERE NO PERSONAL INJURIES.  THE DAILY INSPECTION HAD BEEN PERFORMED AS USUAL AND THE PRE FLIGHT DID NOT SHOW ABNORMALITIES EITHER. THE TOTAL WEIGHT WAS WITHIN LIMITS.                                                                                                                                                                                                                                                                                          1H72 3T4  TRTA9EA    E4EA                 
20060705000192006070500019CE  2006       7          5          CA060613001      120060608G5340504200337       SUPPORT BEAM                            BEECH 100   A100        1152915CE  PWA   PT6   PT6A28           EA  HARTZLHCB4T HCB4TN3     GL  RUDDER QUAD     CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1849018490                                                     UNDER THE PILOTS FLOORBOARDS AT FLIGHT STATION 107, THE PILOTS RUDDER QUADRANT SUPPORT BEAM WAS FOUND CRACKED.  THESE CRACKS WERE FOUND AT 2 OF THE 4 NUT PLATES.  FOUND THESE SAME CRACKS ON 3 OTHER OF OUR AIRCRAFT AROUND THE SAME LOCATIONS.  THE BEAM WAS REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L72 3T4  T  A14CE   E4EA    6  CP40EA    
20060705000202006070500020EU  2006       7          5          CA060613002      120060613G3110                WARNING LIGHT                           SNIAS 350   AS350B3     8680954EU  TMECA ARRIELARRIEL2B         NE                              WARNING PANEL   FALSE INDICATIONW      K   NONE                                                                                            N  FALSE WARNING                                                                 ININSP/MAINT     1                      CA                                                                      UNIT RECEIVED AS INSPECTED.  INSTALLED THE WARNING PANEL IN THE HELICOPTER AND ON GROUND RUN DISCOVERED THAT THE MAIN GEAR BOX RED PRESSURE LIGHT WOULD NOT EXTINGUISH.  WARNING PANEL REPLACED AND THE LIGHT GOES OUT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1G71 3U3  U  H9EU    E00054EN             
20060803002592006080300259GL  2006       8          3          CA060613003      220060611G72616844716         SEAL                                    LKHEED188   188A        5262602WP  ALLSN 501D  501D13      03004GL                              NR 2 ENGINE     LEAKING         W      E   ENGINE SHUTDOWN                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) AFTER A WATER BOMBING RUN CLIMB OUT NR 2 ENGINE WAS SHOWING TWO GALLONS LOW ON OIL. THERE WAS NO OTHER ABNORMAL INDICATIONS, THE CREW DID A PRECAUTIONARY SHUT DOWN. MAINTENANCE FOUND THE SCAVENGE PUMP SEAL TO BE LEAKING OIL BY, THE SEAL WAS REPLACED AND THE ENGINE RUN CHECKED TO BE SERVICABLE.                                                                                                                                                                                                                                                                                                                                                                                                                                    2L74 4T4  TRT4A22    E282                 
20060627002762006062700276CE  2006       6          27         CA060613004      120060612G323350380043        BEARING                                 BEECH 100   A100        1152915CE  PWA   PT6   PT6A28           EA                              MLG ACTUATOR    MISINSTALLED    W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA                                                                      DURING ACT ENDPLAY CHECK AND LUBE OF N/G ACT 50-820208-5,  NOTICED THRUST BEARING IMPROPERLY INSTALLED.  INSTRUCTIONS IN COMPONENT MM ARE TO INSTALL BEARING WITH P/N AWAY FROM GEAR, THIS BEARING HAD BEARING MANUF P/N AND WORD THRUST ON ONE SIDE AND RAYTHEON P/N ON OTHER, ALLOWING YOU TO FOLLOW INSTRUCTIONS AND HAVING A 50% CHANCE OF GETTING IT RIGHT. THIS BEARING WAS INSTALLED BACKWARDS WITH RAYTHEON P/N AWAY FROM GEARS PUTTING ACTUAL THRUST SIDE TOWARDS GEARS OPPOSITE TO THRUST LOADS.   ACT WAS FURTHER INSPECTED AND SMALL AMT OF SPALLING FOUND ON GEARS.  ACT IS BEING RETURNED TO OVERHAUL FACILITY WERE BEARING AND GEARS WILL BE REPLACED. THIS ACT WAS REMOVED FOR IT FIRST ENDPLAY CHECK SINCE LAST OVERHAUL WITH A1L72 3T4  T  A14CE   E4EA                 
20060627002772006062700277    2006       6          27         CA060614001      120060614G7921JR28548A        OIL COOLER      RROYCE      JR28548A                                       RROYCETAY   TAYMK6118        NE                              FUEL OIL        UNSERVICEABLE   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                  VARIOUS                                             5 FUEL COOL OIL COOLERS (FCOC) RE-CALLED FROM SOUTHWEST COOLER SERVICE INC, APPROVED SUPPLIER FOR ROLLS-ROYCE CANADA) DUE TO FAA UNAPPROVED PART NOTIFICATION NR  2005-00187.  ROLLS-ROYCE CANADA HAVE RE-ROUTED 5 SUSPECT UNAPPROVED FCOCS TO SERCK AVIATION (OEM APPROVED SUPPLIER) FOR RE-OVERHAUL.  SERCK AVIATION HAS REPORTED FCOC WITH MISSING; THERMO ADAPTOR, NUTS AND WASHERS FROM END COVERS AND ALSO ONE FCOC MATRIX (CORE) THAT FAILED PRESSURE TEST DUE TO 11 TUBES JOINT (FERRULE) LEAKS.  THE FCOC WERE PREVIOUSLY DECLARED OVERHAULED CONDITION BY SOUTHWEST COOLER SERVICE INC UNDER RRC PURCHASE ORDER.  RRC ENGINEERING AND ROLLS-ROYCE OEM ARE EVALUATING IN SERVICE COOLERS OVERHAULED BY SOUTHWEST COOLER INC.                  4  F          A25NE                
20061213001282006121300128SW  2006       12         13         CA060614004      120060224G6320212030154101    FITTING                                 BELL  212   212         1181420SW  PWA   PT6T  PT6T3       52045EA                              MAIN ROTOR      CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) PILOT REPORTED A FORE-AFT KICK IN THE CYCLIC, AT THE SAME TIME THEY HEARD A NOISE. ON ARRIVAL OF THE AC, INSPECTED THE M/R SYSTEM, SWASHPLATE, SCISSORS AND SLEEVE, TRANSMISSION MOUNTS AND NO DAMAGE WAS FOUND. A/C WAS FLOWN AGAIN AND THE PILOT REPORTED AN INTERMITTENT LATERAL VIBRATION. ON FURTHER INSPECTION, FOUND BOTH EARS ON THE LOWER LIFT LINK FITTING WERE CRACKED. A/C WAS DISASSEMBLED TO ALLOW REPLACEMENT OF THE FITTING, A/C REASSEMBLED AND RETURNED TO SERVICE.  FAILURE OF THIS FITTING WAS A RESULT OF AN INCORRECT FITTING/ATTACH BOLT CONFIGURATION, THERE ARE 2 LOWER LIFT LINK CONFIGURATIONS POSSIBLE.    (TC NR 20060614004)                                                                                1G71 4U4  U  H4SW    E22EA                
20060627002782006062700278NE  2006       6          27         CA060614005      220060609G7200                CASE                                    BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE  HARTZLHCE4A HCE4A3I     NE  ENGINE          LEAKING         W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA            4833                                                      APPROX 20 MIN INTO CRUISE FLIGHT, THE LT LOW OIL PRESSURE LIGHT CAME ON .  THE ENGINE WAS SHUT DOWN AS IT REACHED 50 PSI.  ELECTED TO RETURN TO PLACE OF DEPARTURE AND A SUCCESSFUL LANDING WAS MADE.  UPON STOPPING A LARGE QUANTITY OF OIL WAS FOUND UNDERNEATH LT ENGINE COWL.  MAINTENANCE WAS DISPATCHED AND A COMPLETE REPORT WILL FOLLOW WITH FURTHER FINDINGS.                                                                                                                                                                                                                                                                                                                                                                          2L72 4T4  TRTA24CE   E26NE   5  CP10NE    
20061213001292006121300129CE  2006       12         13         CA060615001      120060613G80006041H190        RELAY                                   BEECH 90    C90         1152913CE  PWA   PT6   PT6A21      52043EA  HARTZLHCB3T HCB3TN3     GL  STARTER         BURNED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) AIRCRAFT WAS ON A OPS 1 INSPECTION BASE . WHILE WORKING ON SNAG 1769A (OIL COMING FROM A/C COMPRESSOR). AFTER REMOVING THE UNSERVICEABLE A/C COMPRESSOR A VISUAL OF THE SURROUNDING AREA REVEALED THAT THE AIR CONDITIONER START RESISTOR PHENOLIC P/N 100-364190-31 WAS BURNED ON BOTH SIDES AND THAT ONE OF THE TERMINALS WAS BROKEN ON THE START RELAY. WE ARE GOING TO REPLACE A/C COMPRESSOR P/N ER206R-25202 , START RELAY P/N 6041H190 , PHENOLIC  P/N 100-364190-31 THAT IS MOUNTED ON BOTH SIDES OF THE A/C START RESISTOR AND SERVICE SYSTEM . (TC NR 20060615001)                                                                                                                                                              1L72 3T4  T  3A20    E4EA    6  CP15EA    
20060627002802006062700280EU  2006       6          27         CA060615002      120060604G5514F50B381003111   GUIDE                                   AMD   FALC50FALCON50MYST2730106EU  GARRTTTFE731TFE73131C   01518NE                              HORIZONTAL STAB BENT            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       8351                                                           GUIDE PLATE SEPARATED FROM HORIZONTAL STAB FILLET, WAS FOUND LYING BETWEEN VERTICAL STABILIZER AND HORIZONTAL STABILIZER.  UNIT HAD BEEN CRUSHED BETWEEN HORIZONTAL STAB AND VERTICAL STAB AS STAB WAS TRIMMED POTENTIAL THAT GUIDE PLATE COULD HAVE MOVED AFT AND JAMMED ELEVATOR LINKAGE.  UNIT WAS REMOVED STRAIGHTENED AND REATTACHED TO HORIZONTAL STAB FILLET ASSEMBLY PER MANUFACTURERS INSTRUCTIONS "SRM SI-20-05, S0-10-04, HORIZONTAL STAB WAS TRIMMED THROUGHOUT ITS ENTIRE RANGE AND NO DISCREPANCIES FOUND.                                                                                                                                                                                                                        2L73 4F4  F  A46EU   E6WE                 
20060627002812006062700281EA  2006       6          27         CA060615003      220060615G7200                ENGINE                                  BEECH 1900  1900C       1154161CE  PWA   PT6   PT6A65B     52043EA  HARTZLHCB4M HCB4MP3     GL  LEFT            SURGES          W      A   UNSCHED LANDING                                                                                 XMJENGINE FLAMEOUT           OVER TEMP                 WARNING INDICATION        CLCLIMB          1                      CA            6914                          PCE32506                    ON CLIMB-OUT, THE AIRCRAFT EXPERIENCED A LEFT ENGINE SURGE WITH HIGH ITT AND LOW OIL PRESSURE INDICATIONS. THE CREW SHUT DOWN THE ENGINE IN FLIGHT AND RETURNED FOR AN UNEVENTFUL LANDING.  MAINTENANCE PERSONNEL REPORTED DEBRIS IN THE EXHAUST AND OIL LEAKING FROM THE ENGINE.  THERE IS ALSO AN UNUSUAL NOISE WHEN THE PROPELLER IS ROTATED BY HAND.  THE ENGINE WILL BE REMOVED TO AN APPROVED OVERHAUL FACILITY FOR INVESTIGATION.                                                                                                                                                                                                                                                                                                        2L72 4T4  TRTA24CE   E4EA    6  CP56GL    
20061213001302006121300130SO  2006       12         13         CA060615004      120060609G76032489418         THROTTLE CABLE                          PIPER PA31  PA31350     7103110SO  LYC   O540  TIO540J2BD  41532EA  HARTZLHCE3Y HCE3YR2A    GL  LT ENGINE       FAILED          W      A   UNSCHED LANDING                                                                                 F  FLT CONT AFFECTED                                                             CLCLIMB          1                      CA                                                                      (CAN) AC DEPARTED  AND A SHORT TIME LATER THE PILOT REPORTED THE LT ENGINE THROTTLE / MANIFOLD WAS SET AT 38 AND WAS NOT RESPONDING. THE PILOT DIVERTED BACK. ON DECENT THE LT ENGINE MANIFOLD STAYED CONSTANT AT 38, THE EGT BEGAN TO RISE, ALONG WITH THE CYLINDER HEAD, AND OIL TEMPERATURE. THE AIRCRAFT LANDED SAFELY WITH BOTH ENGINES RUNNING. ONCE ON THE GROUND THE LT ENGINE WAS SHUTDOWN, TAXIED TO RAMP ON RT ENGINE.   THE LT ENGINE WAS INSPECTED, FOUND TO HAVE LOST ALL ENGINE OIL. THE ENGINE SUSTAINED EXTENSIVE DAMAGE. MAINTENANCE DETERMINED THE LT THROTTLE CABLE IN THE CABIN PEDESTAL HAD FAILED. THE THROTTLE CABLE WIRES HAD SEVERED APPROXIMATELY .3125 FROM THE SWAGED PORTION OF THE ROD END. UNFORTUNATELY ON A RO1L72 3O3  O  A20SO   E14EA   5  CP33EA    
20060803002602006080300260EA  2006       8          3          CA060615005      120060613G3246C3US1563        BOLT                                    DHAV  DHC3  DHC3        2800202EA                                                               MLG WHEEL       FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) WHILE PERFORMING MAIN LANDING GEAR (MLG) WHEEL/SKI REMOVAL AND CHANGE TO WHEELS ONLY, MAINTENANCE FOUND THE RIGHT HAND WHEEL/SKI ATTACH BOLT P/N: C3US156-3 TO BE BROKEN. THE BOLT ATTACHES THE SKI BRACKET ASSEMBLY LINK P/N: C3US108-34 TO THE MLG STRUT AND AXLE. THE BOLT HAS FAILED AT THE START OF THE RADIUS WHERE THE DIAMETER OF THE BOLT CHANGES FROM .500" DIAMETER, TO .750" DIAMETER. IT APPEARS THAT THE BOLT FAILURE OCCURRED ON THE TOOLING MARK.  THIS IS OUR SECOND OCCURRENCE WITHIN 59.4 HOURS AND 115 CYCLES. (TC# 20060615005)                                                                                                                                                                                      1H71 3R      A815                         
20060627002832006062700283    2006       6          27         CA060615006      120060614G2720M4612BFG        ROD END                                                                    WRIGHTR1820 982C9HE2    67020EA  HAMSTD43D   43D51       NE                  BROKEN          W      D   RETURN TO BLOCK                                                                                 F  FLT CONT AFFECTED                                                             TXTAXI/GRND HDL  1                      CA            1243                                                      DURING GROUND OPERATION THE PILOT FELT A "CLUNK" IN THE RUDDER SYSTEM WHILE OPERATING THE SERA SYSTEM.  MAINTENANCE CREWS INVESTIGATED AND FOUND THE SERA LOCK ACTUATOR ROD END HAD BROKEN.  THE ROD END WAS REPLACED, THE SYSTEM WAS FUNCTION CHECKED SERVICEABLE AND THE AIRCRAFT WAS RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                           4  R          E259    6  CP8879    
20061213001312006121300131EU  2006       12         13         CA060616001      120060326G6220704A33633211    SPHERICAL STOP                          SNIAS 350   AS350BA     8680817EU  TMECA ARRIELARRIEL1B    6OO30NE                              MAIN ROTOR      UNSERVICEABLE   W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA       3065                                                           (CAN) A/C HAD ABNORMAL VIBRATION AND WOULD NOT STAY IN TRACK. SPHERICAL STOPS HAD EXCESSIVE RUBBER LOSS AND SEPARATION. INSTALLED NEW SPHERICAL STOPS AND M/R COULD BE BALANCE AND TRACKED WITH NO ABNORMAL VIBRATION. (TC NR 20060616001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3U3  UNCH9EU    E19EU                
20060627002872006062700287CE  2006       6          27         CA060616003      120060530G3340CM358910        SWITCH                                  CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA                              LANDING LIGHT   HOT             W      H   DEACTIVATE SYST/CIRCUITS                                                                        M  OVER TEMP                                                                     CRCRUISE         1                      CA       2006                                                           WHEN THE PILOT WENT TO TURN OFF LANDING LIGHT SWITCH, FOUND TO BE HOT AND THE LANDING LIGHT WOULD NOT TURN OFF, THE SWITCH FINALLY TURNED OFF.  THE SWITCH WAS REPLACED WITH A NEW UNIT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1H71 3O3  ONT3A12    1E10                 
20060627002892006062700289    2006       6          27         CA060616004      120060524G324640289           WHEEL                                                                                                                                   MLG             MISMANUFACTURED W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA                                                                      PURCHASED EIGHT CLEVELAND 40-289 WHEEL ASSEMBLIES NEW FROM FACTORY, RETURNED FIVE ASSEMBLIES DUE TO WHEELS INSPECTED BY EDDY CURRENT AND FOUND SEVERAL CASTING FLAWS (VOIDS) IN BEAD AREAS.  WHEEL ASSEMBLIES RETURNED TO FACTORY FOR INVESTIGATION BY THEIR QA DEPARTMENT, HAVE NOT RECEIVED ANY RESPONSE FROM PARKER AEROSPACE AS OF JUNE 9/06.  TWO WHEEL ASSEMBLIES RETURNED THROUGH KADEX AERO SUPPLY, NO SERIAL NUMBERS LISTED.  THREE WHEEL ASSEMBLIES RETURNED THROUGH AVIALL (CALGARY), SERIAL NUMBERS AS FOLLOWS: 4553/4578, 4581/4554, 4575/NSN.                                                                                                                                                                                                                               
20060705000232006070500023EU  2006       7          5          CA060616005      220060614G7200                ENGINE                                  BRAERO748   HS7482A     4231001EU  RROYCEDART  DART5342         EU  ROTOL R4304 R2124304    EU  NR 2            SHUTDOWN        W      A   UNSCHED LANDING                                                                                 YJ ENGINE STOPPAGE           WARNING INDICATION                                  CRCRUISE         1                      CA            7971                          192902                      (CAN) IN CRUISE, ENROUTE TO DESTINATION, THE NR 2 ENGINE AUTO FEATHERED AND SHUTDOWN.  THE AIRCRAFT DIVERTED AND LANDED WITHOUT FURTHER PROBLEM.  THE NR 2 ENGINE WILL BE REPLACED ON SITE. NO CONCLUSION AS TO THE CAUSE HAVE BEEN ARRIVED AT.    (TC NR 20060616005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 3T4  T  A24EU   A196    6  CP899     
20060803002612006080300261WP  2006       8          3          CA060616006      220060615G7297                CONNECTOR                               BAG   JETSTMJETSTM3101  1500215EU  GARRTTTPE331TPE33110UG  01514WP  ROTOL R333  R333482F12  GL  ENGINE          DAMAGED         W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         XJ ENGINE FLAMEOUT           WARNING INDICATION                                  CLCLIMB          1                      CA            6916                          P63111                      (CAN) AFTER DEPARTURE CLIMBING THROUGH 7500FT THE RIGHT ENGINE TORQUE STARTED TO FLUCTUATE.CREW PULLED THE QRH AND FOLLOWED THE DRILLS AND WERE GETTING 10-20% FLUCTUATION CAUSING THE A/C TO YAW RADICALLY LEFT AND RIGHT AT ALL POWER SETTINGS WITH TTL ON OR OFF SO A PRECAUTIONARY SHUTDOWN WAS PERFORMED AND RETURNED TO BASE WITHOUT INCIDENT. MTCE ENGINE RUNUPS CONFIRMED THE TQ FLUCTUATIONS AND TROUBLESHOOTING FOUND A LOOSE PIN CONNECTION ON THE RT ENGINE STRAIN GAUGE CONNECTOR. THE CONNECTION WAS REPAIRED AND THE A/C WAS RUN UP AND RETURNED TO SERVICE.                                                                                                                                                                     2L72 4T4  TRTA21EU   E4WE    6  CP61GL    
20060627002902006062700290EA  2006       6          27         CA060616008      120060610G5610NP1393222       WINDOW                                  CNDAIRCL600 CL6002B19   1900309EA                                                               COCKPIT         CRACKED         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      CA       16406                                                          THE RT SIDE WINDOW CRACKED WHILE IN CRUISE.  FLIGHT WAS DIVERTED TO MAINTENANCE BASE.  WINDOW REPLACED IN ACCORDANCE WITH AMM.  THIS WINDOW IS A PRE-SERVICE BULLETIN.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA21EA                        
20060627002922006062700292EA  2006       6          27         CA060616009      120060611G5610NP139221        WINDOW                                  CNDAIRCL600 CL6002C10   1390015EA                                                                               CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         APAPPROACH       1                      CA       9276                                                           THE INNER PLY OF THE LT WINDOW CRACKED WHILE ON APPROACH.  WINDOW WAS REPLACED IN ACCORDANCE WITH AMM.  THE WINDOW IS A PRE-SERVICE BULLETIN.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F    RTA21EA                        
20060627002932006062700293WP  2006       6          27         CA060617001      120060609G325010150           STEERING SYS                            CVAC  440   440         2422902WP  ALLSN 501D  501D22      03005GL  HAMSTD54H   54H60       NE  NLG             MALFUNCTIONED   W      O   OTHER                                                                                           S  AFFECT SYSTEMS                                                                LDLANDING        1                      CA       10605                                                          AFTER T/O, DURING L/G RETRACTION, NOSE WHEELS ENTERED W/W IN A RT TURN ATTITUDE, EVIDENT FROM WEAR MARKS ON TIRES AND RUBBER ON INTERIOR WALLS OF W/W.  WHEN A/C LANDED, NOSE WHEELS WERE STILL TURNED TO THE RIGHT, UNKNOWN TO AIRCREW.  CAPT TRIED TO STRAIGHTEN NOSE WHEELS OUT BUT HAD TO TRY A COUPLE TIMES BECAUSE THERE WAS NO RESPONSE FROM STEERING ACTUATOR.  NOSE WHEEL STEERING DID RESPOND TO INPUTS AND AIRCRAFT WAS ABLE TO TAXI.  IT APPEARS THAT ACTUATOR HAD AN UNCOMMANDED STEERING INPUT UPON TAKEOFF AND LOCKED IN THAT POSITION UNTIL LANDING.  ACTUATOR WAS CHANGED AND AIRCRAFT DEEMED SERVICEABLE.  ACTUATOR WAS SENT BACK TO TYPE CERTIFICATE HOLDER OF AIRCRAFT FOR ANALYSIS.                                        2L72 4R4  T  6A6     E282    6  CP906     
20060627002942006062700294WP  2006       6          27         CA060618001      220060616G7250                TURBINE                                 LEAR  45    45LEAR      5170805CE  GARRTTTFE731TFE731*     01518WP                              ENGINE          NICKED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      DURING A WALK AROUND, MAINTENANCE PERSONNEL NOTICED A PAINT CHIPPED INSIDE THE LT THRUST REVERSER.  FURTHER INVESTIGATION FOUND OVER A DOZEN NICKS ON THE 3ND STAGE TURBINE.  ENGINE WILL BE REMOVED AND SENT TO AN HEAVY MAINTENANCE FACILITY AND A LOANER ENGINE WILL BE INSTALLED.                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F4  FRTT00008WIE6WE                 
20060627002962006062700296CE  2006       6          27         CA060618002      120060617G5753                SKIN                                    LEAR  45    45LEAR      5170805CE  GARRTTTFE731TFE731*     01518WP                              RT TE FLAP      BIRD STRIKE     W      O   OTHER                                                                                           O  OTHER                                                                         APAPPROACH       1                      CA                                                                      ON APPROACH, ON FLAIR AIRCRAFT HIT A BIRD.  ONCE ON THE GROUND THE CREW REPORTED TO MAINTENANCE PERSONAL WHO AFTER INSPECTING THE AIRCRAFT FOUND A DENT ON THE RT FLAP BOTTOM SKIN.  DUE TO THE LOCATION OF THE DENT WHICH WAS NOT COVERED UNDER SRM.  SUPPORT ENGINEERING WAS CONTACTED AND A ENGINEERING DISPOSITION WAS ISSUED TO RETURN THE AIRCRAFT INTO SERVICE.  AN INSPECTION OF THE AREA IS REQUIRED APPROXIMATELY EVERY 50 HOUR UNTIL REPAIR IS COMPLETED OR ANOTHER FLAP IS INSTALLED.                                                                                                                                                                                                                                               2L72 4F4  FRTT00008WIE6WE                 
20060627002972006062700297GL  2006       6          27         CA060619001      320060217G6111S90AT4          BLADE           MCAULY      D2A34C58NO  CESSNA185   A185E       2072818CE  CONT  O520  IO520D      17032SO  MCAULY2A34C D2A34C58    GL  PROPELLER       CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            800   705814                              705814          PROPELLER D2A34C58, SERIAL NR 705814, WORK ORDER NR T68807, C-FYJJ.  PROPELLER RECEIVED FOR 10 YEAR OVERHAUL.  LAST OVERHAUL MARCH 1996, NOW 800.5 HOURS SINCE OVERHAUL.  FOUND BLADE S-90AT-4, SERIAL NR C75151YS, CRACKED IN BLADE THREADS, FOUND WITH EDDY CURRENT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3O3  O  3A24    E5CE    5  CP3EA     
20060803002622006080300262CE  2006       8          3          CA060619002      120060612G27315061001736      TAB                                     BEECH 90    C90A        1152911CE  PWA   PT6   PT6A21      52043EA                              ELEVATOR TRIM   CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) CRACK DISCOVERED ON LOWER TAB SURFACE SKIN ADJACENT TO TAB HORN ATTACH RIB. SEE PICTURES ATTACHED.TRIM TAB ASSEMBLY P/N 50-610017-36 REPLACED WITH NEW. ELEVATOR AND TAB ASSEMBLY BALANCED (21.33 IN LBS TAIL HEAVY) AND REINSTALLED. INDEPENDENT CHECK ON R/H TAB AND ELEVATOR INSTALLATION CARRIED OUT - TAB TRAVELS 9.5 DEG NOSE DOWN AND 20.5 DEG NOSE UP. (TC# 20060619002)                                                                                                                                                                                                                                                                                                                                                          1L72 3T4  TRT3A20    E4EA                 
20060627002982006062700298GL  2006       6          27         CA060619003      320060217G6114D4716           HUB             MCAULY      D2A34C58NO  CESSNA185   A185E       2072818CE  CONT  O520  IO520D      17032SO  MCAULY2A34C D2A34C58    GL  PROPELLER       CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            800   705814                              705814          (CAN) PROPELLER D2A34C58-NO, SERIAL NR 705814, WORK ORDER NR T68807, C-FYJJ.  PROPELLER RECEIVED FOR 10 YEAR OVERHAUL.  LAST OVERHAUL MARCH 1996, NOW 800.5 HOURS SINCE OVERHAUL.  FOUND HUB D4716, SERIAL NR 705814, CRACKED IN THREADS THAT THE BLADE RETENTION NUT SCREW INTO, FOUND WITH EDDY CURRENT.                                                                                                                                                                                                                                                                                                                                                                                                                                      1H71 3O3  O  3A24    E5CE    5  CP3EA     
20060803002632006080300263CE  2006       8          3          CA060619004      120060615G71101099100531516   CHANNEL                                 BEECH 90    C90A        1152911CE  PWA   PT6   PT6A21      52043EA                              COWL            CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) THE P/N 109-910053-15 AND -16 COWL SUPPORT CHANNELS WERE FOUND CRACKED IN THE LOWER FLANGE AREA, AND SUBSEQUENTLY REPAIRED. MANY OF THE REPAIRS HAVE ALSO FAILED. IT APPEARS THAT A SUBSTANTIAL AMOUNT OF COWLING WEIGHT RESTS ON THESE CHANNELS. THE REPEAT DAMAGED SUGGESTS THAT THIS AREA IS UNDER DESIGNED. SEVERAL OTHER OPERATOR C90A AIRCRAFT HAVE SHOWN SIMILAR FAULTS. (TC# 20060619004)                                                                                                                                                                                                                                                                                                                                         1L72 3T4  TRT3A20    E4EA                 
20060627002992006062700299EA  2006       6          27         CA060619005      120060606G2910B030212604      B-NUT                                   CNDAIRCL600 CL600*             EA  GE    CF34  CF34*            NE                              HYD SYSTEM      LEAKING         W      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      AFTER TAKEOFF, "NR 2 HYD LOW PRESS" CAUTION MESSAGE WAS DISPLAYED.  THE AIRCRAFT RETURNED TO THE ORIGINATING AIRPORT AND PERFORMED AN EMERGENCY LANDING.  MAINTENANCE FOUND THE FORWARD NR 2 BRAKE ACCUMULATOR CONNECTING HYDRAULIC LINE'S NUT LOOSE (CRJ700/900 IPC 29-17-06, FIG.23-AA1, ITEM NR 90).  THE NUT WAS RE-TORQUED AS PER STANDARD PRACTICES AND NR 2 ENGINE DRIVEN PUMP (P/N 66190-3, S/N K0651) WAS REPLACED AS A PRECAUTION.  NR 2 HYDRAULIC SYSTEM WAS SERVICED AND AIRCRAFT RETURNED TO SERVICE.  NO MAINTENANCE HAS BEEN PREVIOUSLY PERFORMED ON THE HYDRAULIC LINE, NEITHER ON NR 2 BRAKE ACCUMULATOR.  AIRFRAME HOURS WERE: 2625:04 AND CYCLES WERE: 1280.                                                                 2L72 4F4  FRTA21EA   E15NE                
20060627003002006062700300GL  2006       6          27         CA060619006      320060606G6114C2343           HUB             MCAULY      2A36C29     CESSNA180   180C        2072608CE  CONT  O470  O470L       17026SO  MCAULY2A36C 2A36C29     GL  PROPELLER       CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3564 442   591003                                              MCCAULEY PROPELLER 2A36C29-AG, SERIAL NR 591003, WORK ORDER NR T69972, C-FLVF.  PROPELLER RECEIVED FOR 10 YEAR OVERHAUL.  LAST OVERHAUL 1996, NOW 442.5 HOURS SINCE OVERHAUL.  FOUND HUB C2343, SERIAL NR 591003, CRACKED IN THREADS THAT THE BLADE RETENTION NUT SCREW INTO, FOUND WITH EDDY CURRENT.                                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3O3  O  5A6     E273    5  CP880     
20060803002642006080300264GL  2006       8          3          CA060619007      120060425G334010128           LIGHT                                   DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE                              EXTERIOR        SHORTED         W      H   DEACTIVATE SYST/CIRCUITS                                                                        H  ELECT. POWER LOSS-50 PC                                                       CRCRUISE         1                      CA       29                                                             (CAN) PILOT REPORTED STROBE CIRCUIT BREAKER (C/B) POPPED DURING FLIGHT, TROUBLESHOOTING REVEALED INCORRECT C/B INSTALLED (5AMP INSTEAD OF 7.5AMP). NEW C/B INSTALLED AT THAT TIME AND GROUND CHECKED SERVICEABLE. SEVERAL MONTHS LATER PROBLEM RE-OCCURRED DURING FLIGHT BUT GROUND CHECKED OK. WING TIPS REMOVED AND NOTED EVIDENCE OF ARCING FROM TANK INBOARD WALL/RIB AND WING TIP BOSS TERMINAL STRIP STUDS, STATICALLY THERE WAS NO CONTACT, WITH TANKS FULL DURING FLIGHT CONTACT OCCURRED. THE STUDS ON BOSS BAR HAS SUFFICIENT LENGTH TO TRIM 0.25" AND REMAIN IN SAFETY. TIPS RE-INSTALLED WITH PUTTY ON STUDS AND REMOVED TO REVEAL APPROXIMATELY 0.3" CLEARANCE. (TC# 20060619007)                                                  1H71 3R3  RRCA806    5E1                  
20060803002542006080300254NE  2006       8          3          CA060619008      220060425G8550C2L293A         ADAPTER                                 DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE                              ENGINE OIL      CRACKED         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) AIRCRAFT STATICALLY LEAKING ABOVE AVERAGE AMOUNT OF OIL ON HANGAR FLOOR. LOWER BELLY FAIRING/PANEL REMOVED BELOW RUDDER PEDALS, OIL ADAPTER BETWEEN OIL SHUT OFF AND FIREWALL NOTED TO BE SEVERE OF LEAK. ADAPTER REMOVED AND SILVER SOLDER JOINT FOUND CRACKED/LOSS OF ADHESION TO BASE METAL. ADAPTER REPLACED WITH NEW. (TC# 20060619008)                                                                                                                                                                                                                                                                                                                                                                                              1H71 3R3  RRCA806    5E1                  
20060627003032006062700303EU  2006       6          27         CA060619009      120060608G7120                MOUNT                                   BRAERO748   HS7482A     4231001EU  RROYCEDART  DART5342         EU                              COMPRESSOR CASE LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       459324340                                                      WHILE CARRYING OUT MAINTENANCE ON THE RT ENGINE, MAINTENANCE PERSONNEL FOUND LOOSE HARDWARE WHILE OPENING UP THE LOWER PORTION OF THE ENGINE COWLING.  FURTHER INVESTIGATION REVEALED THAT THIS HARDWARE, CONSISTING OF ONE NUT AND ONE BROKEN STUD WITH THE NUT STILL ATTACHED, CAME FROM THE OUTBOARD ENGINE MOUNT FOOT.  AT THIS TIME, IT WAS ALSO DISCOVERED THAT THE OTHER RETAINING NUTS ON THIS FOOT WERE ALSO SLIGHTLY LOOSE.  THE ENGINE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.  AN IN-FIELD REPAIR WILL BE CARRIED OUT ON THE ENGINE.                                                                                                                                                                                     2L72 3T4  T  A24EU   A196                 
20060803002672006080300267NM  2006       8          3          CA060619010      120060618G2497286A1062002     WIRE HARNESS                            BOEING737   737         UTILSYSNM  CFMINTCFM567CFM567B22   13802NE                              NR 2 ENGINE     DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2265 2265                                                      (CAN) ON 18 JUNE 06 DURING TROUBLESHOOTING OF A RECURING NR 2 SOURCE OFF LIGHT ILLUMINATED SNAG, WIRE CHAFFING CAUSING ARCING WAS FOUND BETWEEN FEEDER WIRE HARNESS PART NUMBER 286A1062-002 BOEING IPC 24-11-51-01A ITEM NR 35 AND THE COWLING HINGE PART NUMBER 314-2241-1 BOEING IPC 71-11-02-10 ITEM 76.   INVESTIGATION ALSO REVEALED SOME MINOR CHAFFING ON THE WIRE SHIELDING OF THE NUMBER ONE ENGINE HARNESS IN THE SIMILAR AREA.   A FLEET CAMPAIGN IS RAISED TO INSPECT THE FLEET AND CONFIRM IF THIS IS AN ISOLATED EVENT. BOEING HAS BEEN INFORMED AND WILL BE KEPT ADVISED OF ALL FINDINGS AS THEY COME TO LIGHT.   THIS SDR WILL BE UPDATED WITH ADDITIONAL INFORMATION WHEN AVAILABLE.                                          2L72 4F4  FRTA16WE   E00055EN             
20060803002692006080300269CE  2006       8          3          CA060619012      120060530G5311FS227           FRAME                                   BEECH 100   100BEECH    1152916CE  PWA   PT6   PT6A28           EA                              FUSELAGE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) FRAME, F.S. 227 LOWER FLANGE CRACKED AT RADIUS. CRACK WAS APPROX 4.5 INCHES LEFT AND RIGHT OF A/C CENTRELINE. (TC# 20060619012)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L72 3T4  T  A14CE   E4EA                 
20061213001322006121300132CE  2006       12         13         CA060619013      120060530G5220115430100605    SKIN            BEECH                   BEECH 100   100BEECH    1152916CE  PWA   PT6   PT6A28           EA  HARTZLHCD4N3HCD4N3A     GL  EMERGENCY EXIT  CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                  B8                                                  (CAN) INNER SURFACE LOWER CENTER AREA BETWEEN WINDOW AND LOWER FRAME. CORROSION SPOT 1CM WIDE. WHEN BLENDED MATERIAL THICKNESS WAS INSUFFICIENT. (TC NR 20060619013)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L72 3T4  T  A14CE   E4EA    5  CSTC      
20061213001332006121300133CE  2006       12         13         CA060619014      120060530G57305012006896      SKIN                                    BEECH 100   100BEECH    1152916CE  PWA   PT6   PT6A28           EA  HARTZLHCD4N3HCD4N3A     GL  CENTER WING     CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) SKIN P/N 50-120068-96 CRACKED AT HIGH SHEAR FASTENERS ATTACHING SKIN TO WING ATTACH FITTING. CRACKS (2) ORIGINATE FROM EDGE OF FASTENER COUNTERSINKS AND HEAD TOWARD NEXT FASTENER LOCATION. (TC NR 20060619014)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L72 3T4  T  A14CE   E4EA    5  CSTC      
20060627003062006062700306EU  2006       6          27         CA060620001      120060614G6123                SOLENOID VALVE                          PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  FEATHERING      STICKING        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            1981                                                      FEATHERING SOLENIOD VALVE STICKING INTERMITTENTLY IN FEATHER POSITION AND THEREFORE PROP STAYS FEATHERED AFTER ENGINE START.  FAULT ONLY OCCURS DURING QUICK TURN AROUNDS ON HOT DAYS.  AFTER ENGINE COOLS VALVE OPERATES NORMALY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20060627003082006062700308EU  2006       6          27         CA060620002      120060615G61231310160         SOLENOID VALVE                          PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  FEATHERING      STICKING        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) OVERSPEED GOVERNOR REPLACED WITH AN OVERHAULED UNIT (DUE TO FEATHERING VALVE STICKING INTERMITTANTLY SEE SDR 20060620001) AND DURING FEATHER CHECK THE PROP WOULD NOT COME OUT OF FEATHER.  ELECTRICAL SYSTEM CHECKED.  NO FAULTS FOUND.  ANOTHER SERVICEABLE OVERSPEED GOV.  INSTALLED AND OPERATION CHECKED SERVICEABLE.  AIRCRAFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                 1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20060803002712006080300271NM  2006       8          3          CA060620003      120060620G2422100201022       STATIC INVERTER                         BOEING737   7377CG      13844FANM  CFMINTCFM567CFM567B22   13802NE                              E & E BAY       FAILED          W      H   DEACTIVATE SYST/CIRCUITS                                                                        JB WARNING INDICATION        SMOKE/FUMES/ODORS/SPARKS                            NRNOT REPORTED   1                      CA            149                                                       (CAN) ON THE 20 JUNE 06 WHILE CONDUCTING A SCHEDULED PHASE 3 CHECK. MAINTENANCE FOUND ELEC LIGHT ILLUMINATED ON THE OVERHEAD PANEL. DURING THE TROUBLESHOOTING AN ODOR OF SMOKE WAS NOTICED IN THE E & E BAY. A BITE CHECK WAS CARRIED OUT AND FOUND THE STATIC INVERTER PN 1-002-0102-2090 SN CJ003551 AT FAULT. THE UNIT WAS REPLACED IAW AMM 24-34-21 AND TESTED SERVICEABLE.   PREVIOUS HISTORY: ON 03 MAY 06 THE UNIT WAS SENT OUT ON REPAIR ORDER 64509 TO GET ALERT SB 737-24-1165 CARRIED OUT. THIS MODIFIES THE UNIT FROM A S282T004-10 TO A 1-002-0102-2090. THIS SERVICE BULLETIN GIVES INSTRUCTIONS TO REPLACE THE STATIC INVERTER WITH A NEW OR CHANGED STATIC INVERTER. BOEING AND FEDERAL AVIATION ADMINISTRATION (FAA) RECEIVED 2L72 4F4  FRTA16WE   E00055EN             
20060627003092006062700309CE  2006       6          27         CA060620004      120060615G27506901315         CONTROL LEVER                           LEAR  45    45LEAR      5170805CE  GARRTTTFE731TFE7312     01518WP                              TE FLAPS        FAILED          W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA            102                                                       ON APPROACH INTO TUCSON WHEN FLAP WAS SELECTED TO 8 DEGREE "FLAP FAILED " AMBER CAS ILLUMINATED.  AIRCRAFT LANDED UNEVENTFULLY AND LEARJET INC, TUCSON REPLACED THE FLAP CONTROL LEVER ASS'Y AND RETURNED THE AIRCRAFT INTO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F4  FRTT00008WIE6WE                 
20060628001982006062800198CE  2006       6          28         CA060620005      120060618G2750                FLAP SYSTEM                             LEAR  45    45LEAR      5170805CE  GARRTTTFE731TFE731*     01518WP                              TE FLAPS        MALFUNCTIONED   W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             DEDESCENT        1                      CA                                                                      DURING DESCENT FROM 41,000 FT, AT -54 DEGREES TO 26,000 FT WITH NO FLAP SELECTION.  "FLAP FAILED" AMBER CAS MESSAGE ILLUMINATED.  AT 5000 FT, THE CREW WAS ABLE TO RESET THE FLAP SYSTEM AND AN UNEVENTFUL LANDING WAS MADE. TECHNICIAN FROM LEARJET INC WAS DISPATCHED TO INSPECT AND RETURN THE AIRCRAFT TO SERVICE, AFTER WHICH THE AIRCRAFT FOR FURTHER TROUBLESHOOTING.                                                                                                                                                                                                                                                                                                                                                                    2L72 4F4  FRTT00008WIE6WE                 
20060628001992006062800199CE  2006       6          28         CA060620006      120060620G801151577A1         SOLENOID                                CESSNA207   207A        2073604CE  CONT  O520  IO520F      17032SO  HARTZLHCC3Y HCC3YF1     GL  STARTER         STUCK           W      O   OTHER                                                                                           H  ELECT. POWER LOSS-50 PC                                                       APAPPROACH       1                      CA       11455                                                          UPON DESCENT TO LAND FROM A .4 HRS FLIGHT, THE ELECTRICAL POWER WENT OUT AND WAS UNABLE TO BE RESET BY CYCLING THE MASTER SWITCH.  THE PILOT C/O NORDO PROCEDURES AND LANDED WITHOUT INCIDENT.  UPON INVESTIGATION IT WAS FOUND THAT THE START SOLENOID HAD REMAINED CLOSED UPON START UP CAUSING THE MASTER SOLENOID TO OVERHEAT AND FAIL CAUSING ELECTRICAL POWER TO GO OUT.  THE START SOLENOID AND MASTER SOLENOID WERE REPLACED NEW.  ALL WIRING WAS INSPECTED AND FOUND TO BE GOOD.  AS A PRECAUTIONARY MEASURE THE STARTER AND STARTER DRIVE WERE REPLACED.  THE A/C WAS GROUND RUN AND SYSTEMS CHECKED SERVICEABLE.                                                                                                                     1H71 3O3  O  A16CE   E5CE    5  CP25EA    
20060628002002006062800200NE  2006       6          28         CA060621001      220060615G7200                ENGINE                                  SKRSKYS64   S64E        8142604NE  PWA   JFTD12JFTD12A4A   52047NE                                              FAILED          W      E   ENGINE SHUTDOWN                                                                                 R  PARTIAL RPM/PWR LOSS                                                          HOHOVERING       1                      CA                                                                      A/C INVOLVED IN HELI-LOGGING OPS WITH A/C IN HOVER MADE A MODERATE PWR REDUCTION TO REPOSITION GRAPPLE ON A LOG. AS PWR WAS REDUCED A "WHOOSH" SOUND WAS HEARD AND N1 WARNING HORN ACTIVATED FOR NR 2 ENG.  FLT CREW IDENTIFIED AND CONFIRMED THAT NR 2 ENG ENCOUNTERING A ROLL-BACK AND PROCEEDED TO SHUT ENG DOWN TO COUNTER RISING ENG T5 TEMP. WITH ENG SECURED AND NR T5 TEMP LIMITS EXCEEDED FLT CREW ELECTED TO RESTART NR 2 ENG SINCE A/C HAD 15 KILOMETER FERRY FLT BACK TO ITS SERV LANDING.  ENG WAS SUCCESSFULLY RESTARTED AND A/C RETURNED TO SERV LANDING W/O FURTHER INCIDENT.  A COMPLETE INSPECTION OF ENG AND RELATED LINKAGES REVEALED NOTHING ABNORM.  ENG FUEL FILTER WAS INSPECTED FOR CONTAM WITH NO FAULT FOUND.  AS STA2G72 4U4  U  H4EA    E15EA                
20060803002722006080300272SO  2006       8          3          CA060621002      120060610G32337LM1025013      ACTUATOR                                GRUMANG73   G73T        3951902SO  LYC   O320  O320D1D     41508EA                              MLG             WORN            W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       12308                                                          (CAN) ON THE LT MAIN LANDING GEAR ACTUATOR, THE DOWN LOCK PISTON PIN CIRLIP HAS A LID OVER ITS GROOVE LEAVING THE ACTUATOR UNLOCKED WHEN THE GEAR IS DOWN. ALSO, BECAUSE THE PISTON PIN HAS EXCEEDED ITS LIMIT, THE  SWITCH HAS BEEN DAMAGE LEAVING THE LT INDICATING GREEN LIGHT UNILLUMINATED. THE AIRCRAFT LANDED WITH NO OTHER INCIDENT. AFTER INVESTIGATION: THE SIDE GROVE RETAINING THE CIRCLIP HAS BEEN FOUND WORN, THE ACTUATOR BODY HAS BEEN REPLACED. (TC# 20060621002)                                                                                                                                                                                                                                                              1H72 3R3  O  A783    E274                 
20060628002022006062800202EA  2006       6          28         CA060621003      220060620G8530CL41CCST041CA   CYLINDER HEAD                           CESSNA172   172K        2072430CE  LYC   O320  O320E2D     41508EA  MCAULY1A175 1A175ATM    GL  ENGINE          CRACKED         W      C   ABORTED TAKEOFF                                                                                 ER VIBRATION/BUFFET          PARTIAL RPM/PWR LOSS                                TOTAKEOFF        1                      CA       1023                               L2430227A                   ENGINE RUNNING ROUGH FOUND NR 1 CYLINDER HEAD CRACKED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3O3  ONT3A12    E274    5  NP857     
20060804000192006080400019NM  2006       8          4          CA060621004      120060619G27519660022001      TRANSMITTER                             BOEING727   727227      1384078NM  PWA   JT8   JT8D9A      52048NE                              TE FLAPS        MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      CA                                                                      (CAN) AFTER DEPARTURE, CREW OBSERVED AN OUTBOARD FLAP ASYMMETRY INDICATION. A/C RETURNED TO BASE WHERE MAINTENANCE DISCOVERED A FAULTY POSITION TRANSMITTER. PART WAS REPLACED AND A/C RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L73 4F4  F  A3WE    E2EA                 
20070516001612007051600161EA  2007       5          16         CA060621005      220060620G732286245023        FLANGE                                  PIPER PA44  PA44180     7104402SO  LYC   O360  O360A1H     41514EA  HARTZLHCC2Y HCC2YR2     GL  CARB MOUNT      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1120                                                           (CAN) DURING ROUTINE INSPECTION OF RT ENGINE A .5 INCH CRACK WAS OBSERVED ALONG A SCRIBE LINE ON THE FORWARD FACE OF THE CARB AIR BOX NEAR TO THE LOWER MOUNTING BOLT HOLE . AFTER REMOVAL, (2) ADDITIONAL CRACKS WERE OBSERVED ALONG A SCRIBE MARK NEAR TO THE UPPER MOUNTING HOLES. THESE CRACKS TRAVERSED NEARLY COMPLETELY ACROSS THE MOUNTING FLANGE FACE. IN ADDITION THE MOUNTING HOLE ALIGNMENT BETWEEN THE MOUNTING FLANGE AND THE INNER DOUBLER WERE OFFSET BY APPROXIMATELY .0312 INCH. THIS MAY HAVE INDUCED STRESS THAT LED TO CRACK FORMATION ALONG THESE SCRIBE MARKS. BEFORE A NEW ASSEMBLY WAS INSTALLED THE MOUNTING HOLES WERE REAMED TO ALIGN THE HOLES IN BOTH PLATES. (TC NR 20060621005)                                 1L72 3O3  O  A19S0   E286    5  CP920     
20060628002032006062800203EU  2006       6          28         CA060621006      120060621G73349550179130      PRESSURE SWITCH                         SNIAS 350   AS350B3     8680954EU  TMECA ARRIELARRIEL2B         NE                              FUEL LOW        LEAKING         W      E   ENGINE SHUTDOWN                                                                                 K  FLUID LOSS                                                                    TXTAXI/GRND HDL  1                      CA                                                                      DURING A START, PILOT NOTICED A FUEL PRESSURE WARNING LIGHT NOT EXTINGUISHING.  CONTINUED WITH THE START THROUGH TO IDLE.  THEN SHUT THE AIRCRAFT DOWN AFTER 10 SECONDS AT IDLE.  AFTER SHUT DOWN OPENED UP THE ENGINE COWLING AND NOTICED FUEL ON THE ENGINE DECK.  FUEL WAS COMING FROM THE WEEP HOLE OF THE PRESSURE SWITCH WITH AIRCRAFT BOOST PUMP ON.                                                                                                                                                                                                                                                                                                                                                                                     1G71 3U3  U  H9EU    E00054EN             
20060703000052006070300005EA  2006       7          3          CA060622001      220060621G7313LW18853         NOZZLE                                  PIPER PA31  PA31350     7103110SO  LYC   O540  TIO540J2BD  41532EA  HARTZLHCE3Y HCE3YR2     GL  ENGINE          CONTAMINATED    W      A   UNSCHED LANDING                                                                                 BJ SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION                                  CLCLIMB          1                      CA            592                           L785461A                    TOWER ADVISED PILOT OF SMOKE FROM LEFT ENGINE ON CLIMB-OUT.  MAINTENANCE FOUND CONTAMINATION IN 1 OF THE FUEL INJECTION NOZZLES.  SOURCE COULD NOT BE DETERMINED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L72 3O3  O  A20SO   E14EA   5  CP33EA    
20060804000212006080400021CE  2006       8          4          CA060622002      120060620G2810CCA1550         DRAIN                                   BEECH 99    99          1154002CE  PWA   PT6   PT6A28           EA                              FUEL SYS        BROKEN          W      O   OTHER                                                                                           K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) AFTER FUELING THE AIRCRAFT THE FIRST OFFICER HEARD A SPLASH AND FOUND FUEL LEAKING FROM UNDER THE LEFT WING.  THE T PORTION OF THE FUEL DRAIN HAD FALLEN OUT AND THERE WAS NO WAY TO SHUT THE QUICK DRAIN VALVE OFF.  THE TOP PART OF THE VALVE AND ORING WERE RECOVERED WHEN THE DRAIN VALVE WAS REPLACED. (TC# 20060622002)                                                                                                                                                                                                                                                                                                                                                                                                             1L72 3T4  T  A14CE   E4EA                 
20060804000232006080400023SW  2006       8          4          CA060622003      120060621G5302206031418001    SUPPORT                                 BELL  206   206B        1181511SW                                                               TAIL BOOM       CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       6856                                                           (CAN) FIN ATTACH POINTS WERE BEING INSPECTED AS PER ASB 206-06-107, CF2006-12.  A LARGE CORROSION PIT WAS FOUND ON THE BOTTOM BOLT HOLE.  THE SUPPORT INSTALLATION IS TO BE REPLACED AS PER THE ASB WITH A ONE-PIECE CASTING. (TC# 20060622003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1G71 3U      H2SW                         
20060804000242006080400024WP  2006       8          4          CA060622004      120060622G7720A0582           SWITCH                                  ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              OVERTEMP        STUCK           W      O   OTHER                                                                                           N  FALSE WARNING                                                                 CRCRUISE         1                      CA       21                                                             (CAN) MAIN ROTOR TRANSMISSION OVER TEMP LIGHT CAME ON.  PILOT LANDED AND LET THE AIRCRAFT COOL DOWN.  LIGHT STAYED ON.  TRANSMISSION WAS INSPECTED FOR SIGNS OF OVER TEMP, AND NO DEFECTS WERE FOUND.  OVERTEMP SWITCH WAS FOUND TO BE STUCK IN THE CLOSED POSTION. (TC# 20060622004)                                                                                                                                                                                                                                                                                                                                                                                                                                                           1G71 3O3  O  H11NM   1E4                  
20060804000252006080400025SW  2006       8          4          CA060622005      120060621G2497206075265103    CABLE                                   BELL  205   205A1       1181414SW  LYC   T53   T5313B      41549NE                              STARTER GEN     MELTED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING TURN AROUND CHECK BY THE AME, THE WIRES TO THE STARTER GENERATOR WERE FOUND TO BE SUBJECTED TO  HEAT DAMAGE.  THERE WAS NO INDICATION TO THE PILOT OF ANY DEFECT.  FURTHER INVESTIGATION FOUND THE STARTER GENERATOR WIRE BUNDLE BELOW THE ENGINE DECK TO BE BURNT.  CAUSE OF THE DEFECT IS NOT KNOWN AT THIS TIME.                                                                                                                                                                                                                                                                                                                                                                                                                1G71 4U4  U  H1SW    E17EA                
20060804000262006080400026SO  2006       8          4          CA060623001      120060620G27521216001         DRIVE ASSY                              PIPER PA31  PA31350     7103110SO  LYC   O540  TIO540J2BD  41532EA                              FLAP XMSN       SHEARED         W      D   RETURN TO BLOCK                                                                                 O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA            3105                                                      (CAN) DURING PRE-DEPARTURE CHECK PILOTS NOTED THAT THE RH FLAP WAS NOT RESPONDING TO DOWN SELECTION, LH FLAP MOVEMENT WAS NORMAL. MAINTENANCE CONFIRMED THE SNAG AND T/S REVEALED THE RH FLAP TRANSMISSION WAS NOT DRIVING THE FLAP, FLAP MOTOR AND DRIVE CABLES WERE CHECKED SERVICEABLE. REPLACED RH FLAP TRANSMISSION,FLAPS RIGGED PER PIPER MM AND AIRCRAFT DISPATCHED.                                                                                                                                                                                                                                                                                                                                                                     1L72 3O3  O  A20SO   E14EA                
20060804000282006080400028CE  2006       8          4          CA060623002      120060619G55401015000573      FASTENER        BEECH                   BEECH 1900  1900C       1154161CE  PWA   PT6   PT6A65B     52043EA                              RUDDER SHAFT    LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                  UB71                                                (CAN) RUDDER QUADRANT P/N 101-500057-3 FOUND LOOSE ON INSPECTION. THREE MONEL BLIND RIVETS ATTACHING QUADRANT TO SHAFT ASSY. P/N 114-524025-1 WERE FOUND LOOSE AND DETERMINED TO BE THE CAUSE OF THE QUADRANT LOOSNESS. (TC# 20060623002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4T4  TRTA24CE   E4EA                 
20060804000292006080400029WP  2006       8          4          CA060623003      120060528G6730D2121           SERVO                                   ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              HYDRAULIC SYS   LEAKING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1570                                                           (CAN) UPON INSPECTION THE AFT SERVO WAS FOUND TO BE LEAKING FROM THE PILOT VALVE.  SERVO REPLACED WITH A SERVICEABLE UNIT. (TC# 20060623003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1G71 3O3  O  H11NM   1E4                  
20061213001342006121300134CE  2006       12         13         CA060624001      120060615G2711130909B20       BOLT            BEECH                   BEECH 95    95B55       1152729CE  CONT  O470  IO470L      17026SO  HARTZLHCC3Y HCC3YF2     GL  AILERON         LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2554 2554                                                      (CAN) AILERON TRIM BOLT FOUND MIGRATING OUT OF LINKAGE ARM ON LT AILERON TRIM TAB ASSEMBLY. BOLT WAS NOTED TO BE FINGER-TIGHT ONLY AND NOT SET INTO LOCKING DEVICE. NOTE: BOLT WAS FOUND IN THIS CONDITION AFTER FLIGHT CONTROLS WERE INSTALLED AFTER AIRCRAFT WAS PAINTED BY A THIRD PARTY CONTRACTOR. AS BOLT WAS BEING TIGHTENED DURING RECERTIFICATION, RESISTANCE WAS NOTED ENSURING THE LOCKING PROVISIONS WERE SERVICEABLE.COMPANY PROCEDURES ON AIRCRAFT ACCEPTANCE AFTER THIRD PARTY CONTRACT MAINTENANCE TO BE REVISED TO PREVENT RE-OCCURENCE (TC NR 20060624001)                                                                                                                                                                    1L72 3O3  ORT3A16    3E1     5  CP25EA    
20060804000312006080400031NM  2006       8          4          CA060626001      120060621G571266191042        RIB                                     BOEING727   727225      1384077NM                                                               WING            CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING SCHEDULED INSPECTON, MAINTENANCE FOUND THE NR 1 LEADING EDGE SLAT ACTUATOR WING RIB ATTACH POINT CRACKED. CRACKED MOUNT SUPPORT REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L73 4F      A3WE                         
20060804000332006080400033NE  2006       8          4          CA060626002      220060620G7414SB9RU3          MAGNETO                                 BEECH 18    D18S        1151004CE  PWA   R985  R985AN14B   52008NE                              ENGINE          FAILED          W      A   UNSCHED LANDING                                                                                 E  VIBRATION/BUFFET                                                              CRCRUISE         1                      CA            36                                                        (CAN) INTERNAL FAILURE OF MAGNETO - VISUAL DAMAGE TO GEAR. THIS IS THE SECOND MAGNETO TO FAIL ON THIS OVERHAULED ENGINE (PURCHASED FROM TULSA AERO ENGINE). FIRST MAGNETO FAILED AT 30.3 HOURS FROM TSO. SECOND MAGNETO FAILED AT 36.2 HOURS TSO. S/N ON 1ST MAGNETO IS B33715. BOTH MAGNETOS APPEAR TO HAVE THE SAME INTERNAL PRT FAILURE. (TC# 20060626002)                                                                                                                                                                                                                                                                                                                                                                                   1L72 3R3  R  A765    5E1                  
20060804000382006080400038    2006       8          4          CA060626004      420060622G61224V1827          GOVERNOR                                CNDAIRCL215 CL2151A10   1900320EA                                                               PROPELLER       OVERSPEED       W      E   ENGINE SHUTDOWN                                                                                 F  FLT CONT AFFECTED                                                             CLCLIMB          1                      CA            266                                                       (CAN) AFTER WATER SCOOP, THE LEFT PROP WENT TO OVERSPEED, PROP WAS CONTROLABLE WITH THROTTLE AND POWER LEVER AT 2800 RPM. ENGINE WAS SHUT DOWN AND SECURED. THE A/C RETURNED FOR MAINTENANCE. THE PROP GOVERNOR WAS REPLACED AND THE A/C RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2H72 4R    RTA14EA                        
20060804000422006080400042NE  2006       8          4          CA060626005      320060622G6114                SEAL                                    BAG   JETSTMJETSTM3212  1500217EU                                   MCAULY4HFR344HFR34C652  NE  RT PROP         LEAKING         W      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA       5209 1462                                      881759          (CAN) DURING THE WALK AROUND, THE PILOTS NOTICED OIL DRIPPING DOWN ONE BLADE OF THE RT PROPELLER.  MAINTENANCE WAS NOTIFIED AND THE AME WAS DISPATCHED TO ASSESS. IT WAS DETERMINED THAT A BLADE SEAL HAD FAILED. THE PROPELLER WAS REMOVED FROM THE AIRCRAFT AND SENT TO WESTERN PROPELLER IN EDMONTON FOR REPAIRS. A VERBAL REPORT INDICATED THAT THERE WAS NO DAMAGE OR OBVIOUS CAUSE. ALL SEALS WERE REPLACED. THE PROPELLER WAS RE-INSTALLED AND RETURNED TO BASE THE FOLLOWING DAY.                                                                                                                                                                                                                                                       2L72 4T    RTBA15CAA         6  C3PNE     
20060804000442006080400044EA  2006       8          4          CA060626006      120060622G21301305221         SELECTOR PANEL                          DHAV  DHC8  DHC8311     1386006EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF15      NE  CABIN PRESSURE  UNKNOWN         W      B   EMER. DESCENT                                                                                   J  WARNING INDICATION                                                            CRCRUISE         1                      CA       2374223742                                                     (CAN) DURING FLIGHT CABIN PRESSURE WARNING LIGHT ILLUMINATED AT FLT LVL 230, F/A REPORTED MAIN CABIN DOOR SEAL LEAKING. AIRCRAFT COMMENCED RAPID DECENT AT 3000`/MIN . AFTER NORMAL LANDING AT DESTINATION , AIRCRAFT DEPARTED UNDER MEL FOR UNPRESSURIZED FLIGHT. AFTER ARRIVAL AT MAINTENANCE BASE, MAINTENANCE INSPECTED MAIN CABIN DOOR SEAL AND FOUND SERVICEABLE. CABIN PRESSURE SELECTOR PANEL REPLACED, AIRCRAFT GROUND RUN AND ABLE TO OBTAIN AND MAINTAIN MAXIMUM DIFFERENTIAL. AIRCRAFT RETURNED TO SERVICE. AIRCRAFT HAD PREVIOUS HISTORY OF PRESSURIZATION ISSUES IN AUTO MODE,  CABIN PRESSURE COMPUTER PREVIOUSLY REPLACED, (TC# 20060626006)                                                                                    2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060804000482006080400048EA  2006       8          4          CA060627001      220060623G7250310427801       SNAP RING                               BEECH 90    C90         1152913CE  PWA   PT6   PT6A21      52043EA                              ENGINE BEARING  MISSING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            2998                          PCE24983                    (CAN) WHILE TURNING PROPELLER DURING MAINTENANCE, A METAL-ON-METAL GRINDING NOISE WAS COMING FROM INSIDE L/H ENGINE EXHAUST DUCT. MAINTENANCE REACHED IN THRU EXHAUST STACK OPENING AND TAPPED EXHAUST DUCT "SKI SLOPE" AREA AND HEARD A RATTLE SOUND. ENGINE SPLIT, PT DISC REMOVED AND FOUND BEARING COVER SNAP RING MISSING. THE ENGINE HAS SB1389 COMPLIED WITH AT LAST ENGINE O/H. THIS SB CUTS SLOTS TO KEEP BEARING COVER FROM ROTATING. THE SLOTS IN THE PT SHAFT HOUSING WERE FOUND WORN, WHICH ALLOWS BEARING COVER TO SHIFT CAUSING WEAR IN SNAP RING WHICH RETAINS COVER. OVER THE PERIOD OF ENGINE OPERATION FROM O/H `TILL NOW WE SUSPECT THIS HAS CAUSED THE FAILURE OF THE SNAP RING. THIS IN TURN ALLOWED THE BEARING COVER TO 1L72 3T4  T  3A20    E4EA                 
20060804000492006080400049GL  2006       8          4          CA060627002      220060618G726123070328        OIL TANK                                EMB   145   EMB145ER    3260211SO  ALLSN AE300 AE3007A          GL                              ENGINE          RUPTURED        W      EFB ENGINE SHUTDOWN         ACTIVATE FIRE EXT.      EMER. DESCENT                                   KYAFLUID LOSS                ENGINE STOPPAGE           FLAME/FIRE                CRCRUISE         1                      CA       7913                               CAE312063                   (CAN) A/C N14930/145011, ENGINE NR 2 S/N CAE312063 SUFFERED A COMMANDED IN-FLIGHT SHUTDOWN (CIFSD) DUE TO AN OIL TANK RUPTURE THAT LED TO OIL LEAKAGE AND SUBSEQUENT FIRE.  THE ENGINE WAS SHUT DOWN BY THE CREW AFTER LAV SMOKE, ENGINE FIRE, LOW OIL QUANTITY AND HIGH OIL TEMPERATURE INDICATIONS WERE OBSERVED ENROUTE FROM CRP TO IAH.  THE AIRCRAFT DIVERTED TO VCT SAFELY W/O INCIDENT WHERE THE ENGINE IS BEING REMOVED.  METAL DEBRIS WAS FOUND IN THE EXPOSED OIL TANK THAT APPEARS TO BE FROM INTERNAL WEAR. ENGINE IS PRESENTLY AT ROLLS-ROYCE CANADA UNDER INVESTIGATION.                                                                                                                                                          2L72 4F4  FRTT00011ATTE6CH                
20060804000502006080400050SW  2006       8          4          CA060627003      120060625G6220214030606005    SPINDLE                                 BELL  214   214B1       1182105SW  LYC   T55   T5508D      41555NE                              M/R GEARBOX     BROKEN          W      B   EMER. DESCENT                                                                                   J  WARNING INDICATION                                                            HOHOVERING       1                      CA            694   AME28043                                            (CAN) TRANSMISSION SPINDLE ASSY P/N 214-040-606-005 S/N A12-01304 BROKE IN HALF DURRING FLIGHT, AND THE PILOT HEARD A LOUD BANG AND BEGAN A EMERGENCY LANDING. APON SUCSESSFULL LANDING THE ENGINEER FOUND THE SPINDLE CRACKED IN HALF. DURRING THE SHORT TIME IN THE AIR FOR LANDING THE MAIN DRIVESHAFT OVERTEMPED, ONE OF THE TAIL ROTOR DRIVESHAFTS SCRAPED HALF THE WAY THROUGH, AND THE FORWARD DRIVESHAFT COUPLING WAS REMOVED FOR INSPECTION. NEW SPINDLES, LEFT AND RIGHT, AND DRIVESHAFTS WERE INSTALLED AND AIRCRAFT WAS RETURNED TO SERVICE. THIS IS THE SECOND SPINDLE FALURE WE HAVE HAD THIS MONTH.  THE TWO SPINDLES HAVE BEEN REQUESTED TO BE SENT TO BELL IN TEXAS BY BELL HELICOPTER AND WILL BE SENT OUT THIS WEEK. (TC# 2002G71 4U4  U  H6SW    E4NE                 
20060804000512006080400051WP  2006       8          4          CA060627004      220060627G726031035851        BEARING                                 SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP                              TORQUE SENSOR   FAILED          W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         R  PARTIAL RPM/PWR LOSS                                                          CLCLIMB          1                      CA       964                                P54156                      (CAN) THE FRONT SCAVENGE PUMP DRIVE GEAR SHAFT SHEARED IN THE SCAVENGE PUMP, DUE TO THE SCAVENGE PUMP BUSHING THAT SEIZED FROM OIL STARVATION AND METAL CONTAMINATION CAUSED BY THE TORQUE SENSOR BEARING. THE OIL PRESSURE PUMP SHAFT AND BUSHING ALSO HAVE WEAR ON THEM DUE TO OIL STARVATION. THE TORQUE SENSOR BEARING PART NUMBER 3103585-1 FAILED JAMMING UP THE GEAR CAUSING THE BEARING OUTER RETAINER TO HAVE EXCESSIVE WEAR ON IT. THE INNER AND OUTER BEARING RACES AND BALLS HAVE WEAR DAMAGE ON THEM ALSO DUE TO THE FAILED BEARING.                                                                                                                                                                                               2L72 4T4  TRTA8SW    E4WE                 
             20081229     CE  2008       12         29         CA060627005      120060624G2701                ROLLER                                  CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA  MCAULY1A170 1A170E      GL  CONTROL YOKE    DISLODGED       W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             TXTAXI/GRND HDL  1                      CA                                                                      (CAN) CO-PILOTS CONTROL YOKE GUIDE ROLLER ASSY FELL OUT AND ON INVESTIGATION WAS FOUND THAT WRONG SIZE BOLT WAS INSTALLED. FURTHER INVESTIGATION OF THE REST OF THE FLEET IT WAS FOUND THAT 2 OTHER ACFT HAD THE WRONG BOLT PN AND SIZE INSTALLED. CORRECT BOLT INSTALLED AND ACFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                         1H71 3O3  ONT3A12    1E10    5  NP857     
20060804000602006080400060EA  2006       8          4          CA060627006      120060625G52442153300688      DOOR                                    CNDAIRCL215 CL2151A10   1900320EA                                                               LT ACCESSORY    SEPARATED       W      O   OTHER                                                                                           ED VIBRATION/BUFFET          INFLIGHT SEPARATION                                 NRNOT REPORTED   1                      CA       4124                                                           (CAN) AIRCRAFT WAS COMPLETING A SCOOPING RUN WHEN THE LT HAND DOOR ASSEMBLY PN 215-33006-882 OPENED AND DEPARTED THE AIRCRAFT. CREW WERE ABLE TO LIFT AIRCRAFT OFF WATER AND RETURNED TO BASE WITHOUT FURTHER INCIDENT. INVESTIGATION TO FOLLOW TO DETERMINE THE CAUSE OF DOOR OPENING.                                                                                                                                                                                                                                                                                                                                                                                                                                                         2H72 4R    RTA14EA                        
20060804000622006080400062EA  2006       8          4          CA060628001      220060411G7414M3008           GEAR            SLICK                   ZLIN  242   Z242L       9970204EU  LYC   O360  AEIO360A1B6 41514EA                              DISTRIBUTER     UNSERVICEABLE   W      D   RETURN TO BLOCK                                                                                 E  VIBRATION/BUFFET                                                              TXTAXI/GRND HDL  1                      CA       1185       04040517                                            (CAN) DURING POST REMOVAL TEARDOWN INSPECTION OF MAGNETO ELECTRODE FINGER FOUND BROKEN OFF OF THE DISTRIBUTER GEAR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L71 3O3  O0 A76EU   1E10                 
20060804000632006080400063WP  2006       8          4          CA060628002      120060621G7810D3171           HEAT SHIELD                             ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              EXHAUST         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       140                                                            (CAN) DURING A ROUTINE 50 HR ENGINE INSPECTION, IT WAS NOTED THAT THE SUBJECT HEAT SHIELD, THAT IS INSTALLED ON THE EXHAUST TAILPIPE, WAS FOUND CRACKED. THE CRACK ORIGINATED IN A DOUBLER AREA WHERE THE FORWARD CLAMP IS ATTACHED. THE CRACK LOOKS AS THOUGH IT STARTED FROM A RIVET WHICH ATTACHES THE DOUBLER AND BRACKET, WHICH PROVIDES A MEANS TO ATTACH THE CLAMP TO THE EXHAUST TAIL PIPE. THE PART IN QUESTION HAS 140.3 HRS TIME SINCE NEW. THE AIRCRAFT IN QUESTION HAS 343.5 HOURS SINCE NEW. THE PART HAS BEEN SUBMITTED TO ROBINSON HELICOPTER FOR WARRANTY. (TC# 20060628002)                                                                                                                                                   1G71 3O3  O  H11NM   1E4                  
20060804000662006080400066WP  2006       8          4          CA060628003      120060621G7810C1695           COLLECTOR RING                          ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              EXHAUST         BENT            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       344                                                            (CAN) DURING A ROUTINE 50 HOUR ENGINE INSPECTION, IT WAS NOTED THAT THE L/H EXHAUST COLLECTOR WAS BENT AT THE AFT DOWNPIPE CREASE AREA. DURING FURTHER INVESTIGATION, IT WAS NOTED THAT A CRACK HAD FORMED IN THE SUBJECT AREA. DURING REMOVAL OF THE SUBJECT PART, IT WAS ALSO NOTED THAT THE OUTLET FLANGE THAT FITS INTO THE MUFFLER, WAS DEFORMED AND CRACKED AS WELL. THE SUBJECT PART HAS NOT BEEN REMOVED OR ALTERED SINCE NEW. THE PART HAS BEEN RETURNED TO MANUFACTURER FOR WARRANTY. CONSIDERATION IS BEING MADE THAT THE PART MAY HAVE BEEN PUT IN A STRESSFUL CONDITION WHEN INSTALLED AT THE FACTORY. THE AIRCRAFT HAS 343.5 HOURS SINCE NEW.                                                                                     1G71 3O3  O  H11NM   1E4                  
20060804000672006080400067EU  2006       8          4          CA060628004      120060628G3320BVO320204114    SOCKET                                  AEROSPATR42 ATR42300    8680920EU  PWA   120   PW120            NE  HAMSTD14SF  14SF5       NE  RT WINDOW LIGHT OVERHEATED      W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      NRNOT REPORTED   1                      CA                                                                      (CAN) LAMP SOCKET P/N BVO3202-04-114 OVERHEATED AND SMOKE SMELL NOTED AT R/H CABIN SIDE WINDOW LIGHT. LAMP SOCKET REPLACED. TESTED SERVICEABLE. (TC# 20060628004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2H72 4T4  TRTA53EU   E20NE   6  CP7NE     
20060804000702006080400070NE  2006       8          4          CA060628007      220060608G8530282992          COVER                                   BEECH 18    D18S        1151004CE  PWA   R985  R985AN14B   52008NE                              PUSHRODS        CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            512   210872                                              (CAN) DURING ENGINE DIS-ASSEMBLY FOR CYLINDER REPAIRS, THE PUSHROD COVERS (TUBES) WERE FOUND TO BE HEAVILY DAMAGED UNDER THE CONTACT AREA OF THE SEAL PACKINGS.  THESE PUSHROD COVERS HAD BEEN CHROME PLATED AT THE PREVIOUS OVERHAUL, AND THIS CHROME WAS FOUND TO HAVE BONDED TO THE PACKINGS AND HAD LIFTED AWAY FROM THE PARENT MATERIAL, CAUSING A SERIOUS POTENTIAL LEAK PATH AND/OR BREAKAGE POINT.  I AM NOT AWARE OF ANY APPROVED PROCESS TO CHROME THESE TUBES.  ALL TUBES WERE REPLACED WITH NEW. (TC# 20060628007)                                                                                                                                                                                                                  1L72 3R3  R  A765    5E1                  
20060804000722006080400072EU  2006       8          4          CA060629001      120060626G3260                UPLOCK                                  AEROSPATR42 ATR42300    8680920EU  PWA   120   PW120            NE  HAMSTD14SF  14SF5       NE  MLG             FAILED          W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      CA            2781                                                      (CAN) WHEN THE CREW SELECTED GEAR UP ALL POSITIONS FAILED TO SHOW UP AND LOCKED. THE CREW RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT INCIDENT. MAINTENANCE REPLACED THE RIGHT HAND MAIN LANDING GEAR UPLOCK BOX ASSY. AND THE WEIGHT ON WHEELS UPPER WIRING HARNESS. THE LANDING GEAR WAS FUNCTION CHECKED AND THE AIRCRAFT RETURNED TO SERVICE. (TC# 20060629001)                                                                                                                                                                                                                                                                                                                                                                       2H72 4T4  TRTA53EU   E20NE   6  CP7NE     
20060804000752006080400075EU  2006       8          4          CA060629002      120060619G3297                CONTACT                                 AEROSPATR42 ATR42300    8680920EU  PWA   120   PW120            NE  HAMSTD14SF  14SF5       NE  MLG             FOULED          W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      CA       27455                                                          (CAN) DEPARTING THE LANDING GEAR LEVER WOULD SELECT TO THE UP POSITION. THE AIRCRAFT REURNED TO POINT OF DEPARTURE AND LANDED WITHOUT FURTHER INCIDENT. MAINTENANCE DETERMINED THE GROUND CONTACT FOR THE GEAR LEVER LOCKOUT SOLENOID WAS FOULED. THE CONTACT WAS CLEANED AND A FUNCTION CHECKED PERFORMED PRIOR TO THE AIRCRAFT BEING RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                     2H72 4T4  TRTA53EU   E20NE   6  CP7NE     
20060804000782006080400078CE  2006       8          4          CA060629003      120060628G361024538400        FLANGE                                  CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              TUBE            DEBONDED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       7216                                                           (CAN) WELDED TUBE ASSEMBLY REMOVED FROM AIRCRAFT TO GAIN ACCESS FOR INSPECTION.  WELDED TUBE ASSEMBLY INSPECTED - FLANGE ATTACHED APPEARED TO BE BONDED TO TUBE.  UPON INSTALLATION ON AIRCRAFT - WHEN CLAMP ATTACHING WELDED TUBE ASSEMBLY TO CABIN VENTILATION JUNCTION BOX WAS TORQUED.  THE WELDED TUBE ASSY WAS FREE TO PULL OUT OF FLANGE.  INSERTED WELDED TUBE ASSY BACK INTO FLANGE AND RELEASE THE CLAMP.  FOUND FLANGE HAD A TIGHT METAL TO METAL FIT.  ABLE TO PULL OFF FLANGE WITH SOME FORCE.  FLANGE IS BONDED TO WELDED TUBE ASSEMBLY WITH ADHESIVE.                                                                                                                                                                            1L72 4F4  F  A22CE   E1NE                 
20060804000802006080400080CE  2006       8          4          CA060629004      120060629G531012139881        DOOR FRAME                              CESSNA206   U206G       2073356CE  CONT  O550  IO550F      17042SO  MCAULYD3A34 D3A34C402   GL  FUSELAGE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       5952                                                           (CAN) FORWARD DOOR POST BULKHEAD CRACK DETECTED DURING ACCOMPLISHMENT OF SEB 93-5 CESSNA SERVICE KIT SK206-42 LOWER FORWARD DOORPOST BULKHEAD AND WING STRUT FITTING REINFORCEMENT TO BE INSTALLED. (TC# 20060629004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1H71 3O3  O  A4CE    E3SO    5  CP47GL    
20060804000822006080400082NE  2006       8          4          CA060629005      220060628G8530356996          CYLINDER                                DOUG  DC6   DC6B        3021712WP  PWA   R2800 CB3         52026NE  HAMSTD43E   43E60       NE  ENGINE          CRACKED         W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA            808                           NK510094                    (CAN) DURING CRUISE, NR 1 ENGINE BMEP INDICATION WAS FLUCTUATING, AIRCRAFT HAD A SLIGHT YAW. THE RETARDANT LOAD WAS JETTISONED AND THE ENGINE WAS SHUT DOWN AND PROP FEATHERED. THE AIRCRAFT RETURNED TO BASE. UPON INVESTIGATION NR 15 CYLINDER EAR WAS FOUND CRACKED. THE CYLINDER WAS REPLACED, ENGINE WAS GROUND RUN AND LEAK CHECKED AND THE AIRCRAFT WAS RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                             2L74 4R4  R  6A4     E264    6  CP871     
20061018000752006101800075EU  2006       10         18         CA060629006      120060627G6320DHS43911142     RETAINING NUT   UROCOP                  SNIAS 350   AS350BA     8680817EU  TMECA ARRIELARRIEL1B    6OO30NE                              M/R GEARBOX     BROKEN          W      A   UNSCHED LANDING                                                                                 E  VIBRATION/BUFFET                                                              APAPPROACH       1                      CA       1392       M149                                                (CAN) RETAINING NUT FOR THE INPUT FLANGE ON THE TRANSMISSION (MAIN GEARBOX) BROKE IN 2 PIECES CAUSING THE SPLINED ADAPTER TO BACK OFF, WHICH CAUSED THE HYDRAULIC BELT TO RUN ON THE EDGE OF THE PULLEY. (TC NR 20060629006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1G71 3U3  UNCH9EU    E19EU                
20060804000842006080400084CE  2006       8          4          CA060629007      120060620G213310138001313     OUTFLOW VALVE                           BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA                              CABIN PRESSURE  FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            16                BB170                                   (CAN) THE AIRCRAFT EXPERIENCED A LEAK DOWN OF CABIN PRESSURE.  THE TROUBLE WAS TRACED TO THE FLOW CONTROL PACK UNITS.  BOTH CONTROL UNITS WERE REPLACED WITH OVERHAULED UNITS.  THE UNITS THAT WERE INSTALLED NEVER PROVIDED ENOUGH FLOW FOR PRESURIZATION, HEATING AND COOLING.  WHEN THE OVERHAULER OF THE UNITS WAS CONTACTED, THEY INFORMED US THAT THEY HAD PROBLEMS WITH THEIR CALIBRATION SYSTEM WHICH MADE THE FLOW PACKS PUT OUT MINIMUM AIR.  THEY HAD KNOWN ABOUT THIS PROBLEM FOR TWO MONTHS OR MORE HOWEVER THEY CONTINUED TO PRODUCE AND SELL OVERHAULED UNITS.  OUR COMPANY RECEIVED TWO OVERHAULED UNITS TO REPLACE THESE THAT WERE OVERHAULED IMPROPERLY ALSO.  THE COMPANY SPECIFIED THAT ANY PACKS OVERHAULED BEFORE MAY 19 W1L72 4T4  T  A24CE   E4EA                 
20060804000862006080400086    2006       8          4          CA060629008      420060620G2562                CONTACT         ACK                     CESSNA195   195A        2073110CE  JACOBPR755  R755B2      35007SW                              ELT BATTERY     DEFECTIVE       W      K   NONE                                                                                            L  NO TEST                                                                       ININSP/MAINT     1                      CA                  2385                                                (CAN) THE GOLD PLATING ON THE BATTERY CONTACT IS FLAKING OFF. THE EXPOSED METAL IS NON-CONDUCTIVE AND THEREFORE THE UNIT NO LONGER FUNCTIONS. (TC# 20060629008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1H71 3R3  R  A790    E237                 
20061018000762006101800076EU  2006       10         18         CA060630001      120060405G3246350A41101606    SKID                                    SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1        NE                              MLG             CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) SKID TUBE FOUND CRACKED AT 2 LOCATIONS FORWARD OF THE FORWARD CROSSTUBE AND BOTH FOUND CORRODED BEYOND REPAIRABLE LIMITS WHILE PERFORMING 5000 HR LANDING GEAR INSPECTION. TUBES P/N 350A41-1016-1063 AND-1163 REPLACED WITH SAME. (TC NR 20060630001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1G71 3U3  U  H9EU    E19EU                
20060804000872006080400087CE  2006       8          4          CA060630002      120060629G534705112421        STOP                                    CESSNA172   172P        2072436CE  LYC   O320  O320D2J     41508EA                              SEAT TRACK      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A ROUTINE SEAT REMOVAL PROCEDURE IT WAS NOTICED THAT THE SEAT STOP WAS BROKEN APART AROUND THE FASTENING SCREW HOLE. THERE IS NOT MUCH MATERIAL BETWEEN THE SCREW HOLE AND THE EDGE OF THE STOP WHICH COULD HAVE LED TO A FAILURE OF THIS AFT POSITIONED SEAT STOP. (TC# 20060630002)                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O3  ONT3A12    E274                 
20060804000902006080400090NM  2006       8          4          CA060630003      120060629G27821U109592        ACTUATOR                                BOEING727   727225      1384077NM                                                               SLAT            INOPERATIVE     W      JA  DUMP FUEL               UNSCHED LANDING                                                         N  FALSE WARNING                                                                 CLCLIMB          1                      CA       8225                                                           (CAN) SHORTLY AFTER TAKEOFF, CREW NOTICED THAT THE #8 LEADING EDGE SLAT WAS NOT INDICATING THAT IT WAS RETRACTED. THE CREW REQUESTED FUEL DUMP AND TURN BACK TO DEPARTURE. MAINTENANCE TESTED THE SLAT AND FOUND THE INDICATION SWITCH IN THE ACTUATOR WAS AT FAULT. MAINTENANCE INSTALLED THE INLINE SLAT JUMPER P/N B2T-27-001-01 AND THE SYSTEM TESTED SERVICEABLE. THE AIRCRAFT WAS DISPATCHED WITHOUT FURTHER FAULTS. ACTUATOR TO BE REPLACED ON THE WEEKEND LAYOVER. (TC# 20060630003)                                                                                                                                                                                                                                                    2L73 4F      A3WE                         
20060804000922006080400092CE  2006       8          4          CA060630004      120060630G251005141823        SEAT                                    CESSNA172   172P        2072436CE  LYC   O320  O320D2J     41508EA                              COCKPIT         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) INSPECTION OF SEAT FRAME ASS`Y DURING SCHEDULED MAINTENANCE REVEALED A CRACKED SUPPORT LEG. SAFETY OF SEAT ASS`Y MAY BE COMPROMISED DUE TO THE WEAKENED SUPPORT LEG. (TC# 20060630004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H71 3O3  ONT3A12    E274                 
20060804000962006080400096EU  2006       8          4          CA060630006      120060627G6520350A33020005    GEARBOX                                 SNIAS 350   AS350BA     8680817EU  TMECA ARRIELARRIEL1B    6OO30NE                              TAIL ROTOR      FAILED          W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA       5846 2489                                                      (CAN) TAIL ROTOR GEARBOX CHIP LIGHT ILLUMINATED IN FLIGHT. AIRCRAFT LANDED AND CHIP DETECTOR EXAMINED, MALL AMOUNT OF FERROUS MATERIAL ON DETECTOR.  DETECTOR CLEANED AND SERVICEABILITY CHECK CARRIED OUT.  ON RETURN TO LANDING SITE, SMALL AMOUNT OF FINE HAIR LIKE PARTICLES DISCOVERED.  TAIL ROTOR GEARBOX REMOVED AND SENT TO OVERHAUL FACILITY FOR TEARDOWN AND REPAIR.  SERVICABLE GEARBOX INSTALLED, AIRCARFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                    1G71 3U3  UNCH9EU    E19EU                
20060804001022006080400102EU  2006       8          4          CA060702001      120060613G324616103000        WHEEL                                   BNORM BN2   BN2A26      1520226EU  LYC   O540  O540E4C5    41532EA                              MLG             CRACKED         W      D   RETURN TO BLOCK                                                                                 E  VIBRATION/BUFFET                                                              TXTAXI/GRND HDL  1                      CA                                                                      (CAN) ON TAXI AFTER LDG, A VIBRATION WAS NOTED ORIGINATION ON THE LH LDG GEAR.  IT WAS ORIGINALLY THOUGHT TO BE A WHEEL OUT OF BALANCE.  ON INSPECTION, A CRACK WAS OBSERVED ON THE INNER WHEEL 1/2 OUTBOARD ASSEMBLY.  THE CRACKED RIM WAS REPLACED WITH NEW CLEAVLAND INNER WHEEL 1/2 PN 161-03000. (TC# 20060702001)                                                                                                                                                                                                                                                                                                                                                                                                                         1H72 3O3  O  A17EU   E295                 
20060804001052006080400105NE  2006       8          4          CA060704001      220060506G7321                FUEL CONTROL                            AIRTRCAT802 AT802       0390305SW  PWA   PT6   PT6A67      52043NE                              ENGINE          MALFUNCTIONED   W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             CRCRUISE         1                      CA                                                                      (CAN) DURING FORMATION FLIGHT THE PILOT REDUCED POWER.  WHEN POWER WAS RE-APPLIED THE ENGINE WOULD NOT RESPOND INITIALLY TO THROTTLE INPUT.  POWER INCREASED AFTER 7 TO 8 SECONDS.  THE FUEL CONTROL UNIT WAS SUBSEQUENTLY REPLACED.  PWC WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                              1L71 3T4  TNCA19SW   E26NE                
20060804001072006080400107EA  2006       8          4          CA060704002      220060527G7210                GEARBOX                                 BEECH 99    99          1154002CE  PWA   PT6   PT6A28           EA                              ENGINE          SPALLED         W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                          40252                       (CAN) THE ENGINE CHIP DETECTOR WARNING ANNUNCIATED IN FLIGHT.  THE ENGINE WAS SHUT DOWN AND THE AIRCRAFT DIVERTED TO AN ALTERNATE AIRPORT.  SUBSEQUENT INSPECTION REVEALED SPALLING OF THE FIRST STAGE REDUCTION GEARBOX GEARING. (TC# 20060704002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L72 3T4  T  A14CE   E4EA                 
20060804001092006080400109NE  2006       8          4          CA060704003      220060530G7261                ENGINE                                  AEROSPATR72 ATR72212A   8680902EU  PWA   PW120 PW127            NE                                              LEAKING         W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         KJ FLUID LOSS                WARNING INDICATION                                  CLCLIMB          1                      CA                                          AK0001                      (CAN) DURING CLIMB THE ENGINE WAS REPORTED TO LOSE OIL PRESSURE.  THE ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC# 20060704003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2H72 4T4  TRTA53EU   E20NE                
20060804001102006080400110EA  2006       8          4          CA060704004      220060515G7250                TURBINE BLADES                          BEECH 90    C90         1152913CE  PWA   PT6   PT6A21      52043EA                              TURBINE SECTION FRACTURED       W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         O  OTHER                                                                         CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB THE ENGINE EMITTED A LOUD NOISE AND WAS SHUT DOWN IN FLIGHT.  THE AIRCRAFT DIVERTED FOR AN UNSCHEDULED LANDING WHICH RESUTED IN AIRFRAME DAMAGE.  SUBSEQUENT INSPECTION REVEALED FRACTURED COMPRESSOR TURBINE BLADES.  P&WC WILL MONITOR INVESTIGATION OF THE BLADES AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC# 20060704004)                                                                                                                                                                                                                                                                                                                                                                                            1L72 3T4  T  3A20    E4EA                 
20060804001562006080400156EA  2006       8          4          CA060704005      220060606G7321                FUEL CONTROL                            DHAV  DHC6  DHC6        2802606EA  PWA   PT6   PT6A27      52043EA                              ENGINE          MALFUNCTIONED   W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) THE ENGINE WAS REPORTED TO EXHIBIT TORQUE FLUCTUATIONS IN CLIMB AND WAS SHUT DOWN IN FLIGHT. THE FUEL CONTROL UNIT WAS SUBSEQUENTLY REMOVED FOR INVESTIGATION.  P&WC WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC# 20060704005)                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H72 3T4  TRTA9EA    E4EA                 
20060804001572006080400157NE  2006       8          4          CA060704006      220060607G7320                EEC                                     LEAR  60    60LEAR      5170707CE  PWA   305   PW305A      52128NE                              ENGINE          FAILED          W      O   OTHER                                                                                           XJ ENGINE FLAMEOUT           WARNING INDICATION                                  DEDESCENT        1                      CA                                                                      (CAN) THE ENGINE FLAMED OUT IN DESCENT.  THE EVENT WAS LATER DUPLICATED DURING FLIGHT TEST.  THE EEC WAS EXCHANGED AND THE PROBLEM COULD NOT BE DUPLICATED.  THE AIRCRAFT WAS RETURNED TO SERVICE.  P&WC WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC# 20060704006)                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F4  FRTA10CE   E35NE                
20060804001582006080400158EA  2006       8          4          CA060704007      220060611G7230                COMPRESSOR                              BEECH 90    C90         1152913CE  PWA   PT6   PT6A34      52043EA                              ENGINE          DAMAGED         W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA                                          RB0182                      (CAN) IN CRUISE, THE ENGINE WAS REPORTED TO EMIT A NOISE FOLLOWED BY A LOSS IN POWER.  THE ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED.  POST FLIGHT INSPECTION REVEALED COMPRESSOR DAMAGE.  P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC# 20060704007)                                                                                                                                                                                                                                                                                                                                                                                                                                          1L72 3T4  T  3A20    E4EA                 
20060804001592006080400159NE  2006       8          4          CA060704008      220060609G7261310047001       ELBOW                                   BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE  HARTZLHCE4A HCE4A3I     NE  OIL SYSTEM      FRACTURED       W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE THE ENGINE LOW OIL PRESSURE WARNING ANNUNCIATED.  THE ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED FOR AN UNSCHEDULED LANDING.  SUBSEQUENT INSPECTION REVEALED THE REDUCTION GEARBOX PRESSURE OIL ELBOW IMPROPERLY SECURED AND FRACTURED.  P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC# 20060704008)                                                                                                                                                                                                                                                                                                                                                                          2L72 4T4  TRTA24CE   E26NE   5  CP10NE    
20060804001622006080400162    2006       8          4          CA060704009      420060613G3418                STALL WARNING                           CNDAIRCL601 CL6013A     8070802EA                                                                               FALSE ACTIVATIONW      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      CA                                                                      (CAN) THE FOLLOWING WAS REPORTED BY THE PILOT; "THE STALL WARNING HORN SOUNDED, STICK SHAKER ACTIVATED FOLLOWED BY THE PUSHER AT FL320 DURING CLIMB.  R AFCS WAS ENGAGED AND COUPLED TO CO-PILOTS FD AT THE TIME.  WHEN THE PILOT GRABBED THE YOKE THE SHAKER ACTIVATED ONE MORE TIME.  THE AFCS WAS DISENGAGED AND THE NOSE WAS LEVELLED. THE STALL HORN AND STALL LIGHTS REMAINED ON.  AN EMERGENCY WAS DECLARED AND THE AIRCRAFT RETURNED TO OWN BASE.  LANDING WAS UNEVENTFUL."   THE FOLLOWING FLIGHT TO THE SERVICE CENTRE WAS UNEVENTFUL AND THE STALL PROTECTION SYSTEM WAS TROUBLESHOT WITH NO FAULT FOUND. THE FDR DATA WAS ANALYSED AND SHOWED THAT, DURING CLIMB OUT, AT FL327 THE AIRSPEED HAD SLOWED TO 155 KIAS, A SPEED CONSIST2L72 4F    RTA21EA                        
20060804001662006080400166NE  2006       8          4          CA060704010      220060613G7200                ENGINE                                  LEAR  60    60LEAR      5170707CE  PWA   305   PW305A      52128NE                                              MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 BJ SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION                                  CLCLIMB          1                      CA                                          305269                      (CAN) IN CLIMB THE CREW REPORTED SMOKE AND OIL SMELL IN THE CABIN ACCOMPANIED BY AN ENGINE CHIP DETECTOR WARNING.  THE CREW DECLARED AN EMERGENCY AND THE FLIGHT WAS DIVERTED TO POINT OF ORIGIN.  PWC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC# 20060704010)                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F4  FRTA10CE   E35NE                
20060804001732006080400173NE  2006       8          4          CA060704011      220060628G73217045402L2       FUEL CONTROL                            SKRSKYS64   S64E        8142604NE  PWA   JFTD12JFTD12A4A   52047NE                              ENGINE          FAILED          W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      CA       4527 313                           672488                      (CAN)  AFTER SETTING A TURN OF LOGS DOWN ON LOG LANDING WITH A LT CROSS WIND, ACFT TURNED FULLY INTO WIND & BEGAN A CLIMB BACK UP HILL TO LOGGING UNIT WITH APPROXIMATELY 60% TORQUE INDICATED. AFTER ABOUT 7-10 SECONDS INTO CLIMB, N1 UNDERSPEED WARNING HORN SOUNDED. FLT CREW REDUCED POWER & OBSERVED N2 NEEDLE FOR NR 2 ENG DECREASING ON TRIPLE TACH. CO-PILOT NOTICED NR 2 ENG N1 SPEED AT 35% & T5 TEMP STABLE AT 465 DEGREES C. CREW ELECTED TO SHUTDOWN NR 2 ENG & MOTOR TO COOL T5. AN ATTEMPT TO RESTART ENG MADE & THEN ABORTED DUE TO ENG NOT ACCELERATING PAST 35% N1. ACFT LANDED WITHOUT FURTHER INCIDENT. A COMPLETE INSPECTION REVEALED NOTHING ABNORMAL. AN ENGINE START ATTEMPTED & ABORTED DUE TO ENG NOT BEING ABLE TO A2G72 4U4  U  H4EA    E15EA                
20060804001762006080400176NE  2006       8          4          CA060704012      220060615G7200                ENGINE                                  BEECH MU300 400A        1155402CE  PWA   JT15  JT15D5      52112NE                                              FLAMED OUT      W      A   UNSCHED LANDING                                                                                 XJ ENGINE FLAMEOUT           WARNING INDICATION                                  CRCRUISE         1                      CA                                          100208100209                (CAN) DURING CRUISE AT FL380 (AND APPROACHING CLOUD TOP) BOTH ENGINES WERE THROTTLED BACK IN POWER BY THE CREW PRIOR TO ENGAGING ANTI-ICE.  BOTH ENGINES FLAMED OUT.  THE ENGINES WERE SUBSEQUENTLY RE-STARTED IN FLIGHT AND THE AIRCRAFT DIVERTED. POST-EVENT INSPECTION REVEALLED NO ENGINE ANOMOLIES. P&WC WILL INVESTIGATE THE EVENT AND WILL REPORT ON ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                        2H72 4F4  FRTA16SW   E25EA                
20060804001782006080400178NE  2006       8          4          CA060704013      220060619G7250                ENGINE                                  AEROSPATR72 ATR72              EU  PWA   PW120 PW127            NE                                              MALFUNCTIONED   W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) IN CRUISE THE ENGINE WAS REPORTED TO EXHIBIT TORQUE AND POWER TURBINE SPEED FLUCTUATIONS.  THE ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC# 20060704013)                                                                                                                                                                                                                                                                                                                                                                                                                                                              2H72 4T4  TRT        E20NE                
20060804001792006080400179NE  2006       8          4          CA060704014      220060618G73218237002         FUEL CONTROL                            CESSNA560   560XL       2076702CE  PWA   545   PW545A           NE                              ENGINE          MALFUNCTIONED   W      E   ENGINE SHUTDOWN                                                                                 FJ FLT CONT AFFECTED         WARNING INDICATION                                  DEDESCENT        1                      CA                                                                      (CAN) DURING DESCENT, THE ENGINE WOULD NOT RESPOND TO THROTTLE INPUTS FOR POWER REDUCTION.  THE ENGINE WAS SHUT DOWN ON FINAL APPROACH.  THE FUEL CONTROL UNIT WAS SUBSEQUENTLY REPLACED. (TC# 20060704014)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA22CE   E00059EN             
20060804001812006080400181NM  2006       8          4          CA060704015      120060619G2120                SMOKE                                   DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              CABIN           DETECTED        W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      DEDESCENT        1                      CA                                          CD0228                      (CAN) ON DESCENT THE CREW REPORTED SMOKE IN THE CABIN AIR.  AN EMERGENCY WAS DECLARED AND THE AIRCRAFT LANDED AT POINT OF DESTINATION.  P&WC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC# 20060704015)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2H72 4T4  FRTA55NM   E35NE                
20060804001832006080400183NE  2006       8          4          CA060704016      220060621G73103031829         TUBE                                    PIAGIOP180  P180        6960204EU  PWA   PT6   PT6A66      52043NE                              FUEL SYS        FRACTURED       W      O   OTHER                                                                                           XJ ENGINE FLAMEOUT           WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) THE ENGINE FLAMED OUT IN CRUISE.  SUBSEQUENT INSPECTION REVEALLED A FRACTURED FUEL SYSTEM P3 AIR TUBE. (TC# 20060704016)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H72 3O4  TRTA59EU   E26NE                
20060804001852006080400185NM  2006       8          4          CA060704017      120060625G7931312244801       PRESSURE SWITCH                         BOMBDRDHC8  DHC8402     1390042NM  PWC   150   PW150A           EA                              OIL SYS         FAILED          W      E   ENGINE SHUTDOWN                                                                                 N  FALSE WARNING                                                                 CRCRUISE         1                      CA                                                                      (CAN) IN FLIGHT, THE CREW OBSERVED A LOSS OF ENGINE OIL PRESSURE INDICATION AND THE ENGINE WAS SHUTDOWN.  THE ENGINE OIL PRESSURE SWITCH WAS SUBSEQUENTLY REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC# 20060704017)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2H72 4T4  TRTA13NM   E00062EN             
20060804001862006080400186NE  2006       8          4          CA060704018      220060627G72613007389         ADAPTER                                 CESSNA208   208         2073702CE  PWA   PT6   PT6A114     52043NE                              OIL SYS         FRACTURED       W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) AT TOP OF CLIMB, ENGINE TORQUE WAS SEEN TO FLUCTUATE FOLLOWED BY AN ENGINE LOW OIL PRESSURE WARNING.  THE ENGINE WAS SHUT DOWN IN FLIGHT AND A DEAD-STICK LANDING ACCOMPLISHED.  SUBSEQUENT INSPECTION REVEALED EXTERNAL OIL LEAKAGE ASSOCIATED WITH A FRACTURED REDUCTION GEARBOX PRESSURE OIL ADAPTER.  P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC# 20060704018)                                                                                                                                                                                                                                                                                                                               1H71 3T3  TNTA37CE   E4EA                 
20060804001882006080400188NE  2006       8          4          CA060704019      220060627G7532                BLEED VALVE                             PILATSPC12  PC12        7090550EU  PWA   PT6   PT6A67B     52043NE                              ENGINE          DIRTY           W      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE, THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY FLAMES FROM THE EXHAUST AND POWER FLUCTUATIONS.  THE PILOT REDUCED ENGINE POWER AND ACCOMPLISHED AN UNSCHEDULED LANDING.  SUBSEQUENT INSPECTION FOUND THE ENGINE COMPRESSOR BLEED VALVE TO BE STIFF AND FULL OF SAND,  THE BOV WAS CLEANED AND THE ENGINE RAN NORMALLY. (TC# 20060704019)                                                                                                                                                                                                                                                                                                                                                                                   1L71 3T4  TRTA78EU   E26NE                
20060804001902006080400190EA  2006       8          4          CA060704020      120060703G2910AN62498         CHECK VALVE                             CNDAIRCL215 CL2151A10   1900320EA                                                               HYD SYSTEM      CRACKED         W      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  NRNOT REPORTED   1                      CA       96   96                                                        (CAN) DURING FIRE FIGHTING OPERATIONS WATERDROP , HYDRAULIC FAILURE OCCURRED. AIRCRAFT LANDED AFTER EMERGENCY LANDING GEAR EXTENSION WITH BOMB DOORS OPEN AND WAS TOWED OFF RUNWAY. THIS IS THE SECOND FAILURE  ON THE SAME AIRCRAFT IN THE SAME POSITION WE HAVE HAD THIS SUMMER FROM CHECK VALVE FAILURE. NEW STAINLESS VALVES HAVE BEEN ORDERED TO COMPLY WITH SUGGESTED CANADAIR SERVICE BULLETIN BUT HAVE NOT ARRIVED. WE HAD TO USE THE OLD STYLE ALUMINUM CHECKVALVE WHEN IT WAS REPLACED EARLIER IN THE SPRING. SEE REFERENCE PREVIOUS SDR #20060427007 DATED MAY 12, 2006. (TC# 20060704020)                                                                                                                                           2H72 4R    RTA14EA                        
20060804001922006080400192EA  2006       8          4          CA060704021      120060702G291082970009325     LINE                                    DHAV  DHC8  DHC8311     1386006EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF15      NE  HYD SYSTEM      LEAKING         W      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  DEDESCENT        1                      CA                                                                      (CAN) ENROUTE AIRCRAFT REPORTED LOSS OF NR 2 HYDRAULIC SYSTEM QUANTITY. ALTERNATE GEAR EXTENSION SELECTED FOR ARRIVAL , NORMAL LANDING. MAINTENANCE INSPECTION FOUND NR 2 ENGINE DRIVEN HYDRAULIC PUMP PRESSURE LINE LEAKING, LINE REPLACED. HYD PUMP REPLACED DUE TO UNKNOWN TIME OPERATING WITHOUT FLUID. AIRCRAFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                       2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060804001962006080400196EA  2006       8          4          CA060705001      120060702G79314120T16P01      TRANSDUCER                              CNDAIRCL600 CL6002D24   1390016EA  GE    CF34  CF348E5     30015NE                              OIL PRESSURE    MALFUNCTIONED   W      E   ENGINE SHUTDOWN                                                                                 O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA       2                                  GEE194466                   (CAN) DURING RIGHT ENGINE WINDMILL RELIGHT, RIGHT ENGINE OIL PRESSURE AT 0 PSI UNTIL 24% N2. AT 34% N2, RIGHT OIL PRESSURE AT 3 PSI. ENGINE SHUT DOWN AND RTB SINGLE ENGINE. NOTE: DURING CRUISE PRIOR TO ENGINE SHUTDOWN, RIGHT ENGINE OIL PRESSURE WAS CONSTANTLY 10 PSI BELOW LEFT ENGINE OIL PRESSURE. (TC# 20060705001)                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F4  FRTA21EA   E00063EN             
20060804001972006080400197NE  2006       8          4          CA060705002      220060705G7230                COMPRESSOR                                                                 PWA   PT6   PT6A135     52043NE                              ENGINE          BIRD INGESTION  W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN)   DAMAGE TO ENGINE COMPRESSOR CAUSED BY BIRDSTRIKE. COMPRESSOR DAMAGE WAS REPAIRED AND ENGINE RETURNED TO SERVICE. (TC# 20060705002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             4  T          E4EA                 
20060804001982006080400198NM  2006       8          4          CA060705004      120060704G612087620130101     SHAFT                                   DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF23      NE  NR 1 PROPELLER  BROKEN          W      E   ENGINE SHUTDOWN                                                                                 F  FLT CONT AFFECTED                                                             DEDESCENT        1                      CA       20301                                                          (CAN) LOSS OF PROPELLER CONTROL DUE TO BROKEN ENGINE CONTROL SPRING STRUT; THE FAILURE OCCURRED DURING FLIGHT AND DISABLED CONTROL OF THE NO 1 PROPELLER. THE EMERGENCY FUEL SHUT-OFF HAD TO BE OPERATED TO SHUT THE ENGINE DOWN AFTER LANDING. AT THE TIME OF THE INCIDENT, THE AIRCRAFT HAD ATTAINED 20301:00 HOURS AND 39275 CYCLES. THE OPERATOR IS PRESENTLY CARRYING OUT A CAMPAIGN OF THEIR FLEET IN AN EFFORT TO AVOID ANY RECURRENCE.   (TC# 20060705004)                                                                                                                                                                                                                                                                              2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060804001992006080400199CE  2006       8          4          CA060705005      120060705G3320S18802          RHEOSTAT                                CESSNA185   A185E       2072818CE  CONT  O520  IO520D      17032SO                              CABIN LIGHTS    MALFUNCTIONED   W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       3560                                                           (CAN) AIRWORTHINESS DIRECTIVE SEARCH ON TRANSPORT CANADA`S WEB SITE DID NOT SHOW 93-24-15 APPLYING TO THIS AIRCRAFT. IT APPEARS THAT THE MODEL APPLICABILITY SECTION OF THE FAA AIRWORTHINESS DIRECTIVE IS INCORRECT. (TC# 20060705005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1H71 3O3  O  3A24    E5CE                 
20060807000022006080700002CE  2006       8          7          CA060705008      120060628G3230M710501         MOTOR                                   BEECH B300  B300        1159232CE  PWA   PT6   PT6A60A     52043NE                              HYD SYSTEM      MALFUNCTIONED   W      O   OTHER                                                                                           J  WARNING INDICATION                                                            APAPPROACH       1                      CA            388                                                       (CAN) DURING APPROACH LANDING GEAR WOULD NOT EXTEND NORMALLY AND 2 AMP CONTROL CIRCUIT BREAKER HAD OPENED. LANDING GEAR WAS LOWERED USING MANUAL SYSTEM AND UNEVENTFUL LANDING CARRIED OUT. MAINTENANCE FOUND 60 AMP LANDING GEAR CIRCUIT BREAKER OPEN (IN LH WING). REPLACED LANDING GEAR MOTOR (RIGHT POWER PACK) WITH OVERHAULED SPARE. RESET CIRCUIT BREAKERS AND GROUND TESTED LANDING GEAR OPERATIONS. EXPERIENCE HAS SHOWN THAT THESE MOTORS ARE PRONE TO PREMATURE FAILURE OR EXCESSIVE CURRENT DRAW.                                                                                                                                                                                                                                   2L72 4T4  TRTA24CE   E4EA                 
20060807000032006080700003NM  2006       8          7          CA060706001      120060703G291065C268091131    LINE                                    BOEING737   737522      138449FNM  CFMINTCFM56 CFM563C1    13802EU                              HYDRAULIC SYS   CRACKED         W      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) #1 ENGINE HYDRAULIC PUMP CONTROL LIGHT ILLUMINATED IN FLIGHT ON CLIMB FROM LA GUARDIA. AIRCRAFT CONTINUED THE FLIGHT. UPON INVESTIGATION IT WAS FOUND THAT A HYDRAULIC LINE FOR THE "A" SYSTEM PRESSURE MODULE WAS CRACKED. LINE REPLACED AND FLUID LEVEL SERVICED. AIRCRAFT RELEASED FOR SERVICE.  TIMES: 37201:46   CYCLES: 22712 (TC# 20060706001)                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA16WE   E21EU                
20060807000092006080700009SW  2006       8          7          CA060706002      120060704G6210204011250001    BLADE                                   BELL  205   205A1       1181414SW  LYC   T53   T5313B      41549NE                              MAIN ROTOR      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1988                                                           (CAN) CRACK ON BOTH SIDES OF BLADE BOLT BORE.  TRAVELLING IN CHORDWISE DIRECTION.  THE LEADING EDGE CRACK TRAVELS RIGHT TO THE LEADING EDGE AND THE TRAILING EDGE CRACK IS APPROXIMATLEY 6 INCHES LONG.  IT APPEARS ALL DOUBLERS ON THE LOWER PART OF THE BLADE ARE CRACKED. (TC# 20060706002)                                                                                                                                                                                                                                                                                                                                                                                                                                                  1G71 4U4  U  H1SW    E17EA                
20060807000202006080700020NE  2006       8          7          CA060706003      220060704G7532310562601       CONNECTING ROD                                                             PWA   JT15  JT15D1      52060NE                              BLEED VALVE     WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) PRATT & WHITNEY CANADA OVERHAUL MANUAL 3037323 REV.22, SECTION 72-30-07, PARAGRAPH 88-4 MISTAKENLY CALLS FOR NICKEL PLATING IN ACCORDANCE WITH SPOP 62. SPOP 62 IS A FLORESCENT PENETRANT INSPECTION PROCEDURE. IT IS UNDERSTOOD THAT THE MANUAL SHOULD RATHER CALL FOR SPOP 26 WHICH IS A NICKEL PLATING SPEC. (TC# 20060706003)                                                                                                                                                                                                                                                                                                                                                                                                                4  F          E1NE                 
20060807000612006080700061NM  2006       8          7          CA060706004      120060702G24331032573         TRU                                     BOEING727   727243      138408DNM  PWA   JT8   JT8D9A      52048NE                              NR 2            SMOKE           W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      TXTAXI/GRND HDL  1                      CA                                                                      (CAN) WHILE AIRCRAFT WAITING ON THE GATE TO BOARD PASSENGERS FOR DEPARTURE, SMOKE WAS OBSERVED IN THE COCKPIT. CAUSE OF SMOKE WAS DETERMINED TO BE THE NR 2 TRANSFORMER RECTIFIER. UNIT REPLACED WITH NO FURTHER DEFECTS.  (TC# 20060706004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L73 4F4  FRTA3WE    E2EA                 
20060807000642006080700064EU  2006       8          7          CA060706005      120060622G21509599060114      A/C PACK                                PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL                  FAILED          W      HA  DEACTIVATE SYST/CIRCUITSUNSCHED LANDING                                                         B  SMOKE/FUMES/ODORS/SPARKS                                                      CLCLIMB          1                      CA       5380                                                           (CAN) PILOT REPORTED THAT ECS WAS SELECTED ON AT PREFLIGHT CHECK. NO PROBLEM NOTICED. SOON AFTER ROUTINE TAKEOFF AN ODOUR WAS PREVALENT IN COCKPIT. ECS SYSTEM WAS DEACTIVATED AND ODOUR DISSIPATED ALMOST IMMEDIATELY. AIRCRAFT RETURNED TO PLACE OF DEPARTURE WITH NO FURTHER FAULTS. PASSENGERS DEBOARDED AND CAPTAIN PERFORMED GROUND RUN TO TEST ECS. ODOUR RETURNED AS SOON AS ECS SELECTED ON. ECS SYSTEM WAS AGAIN DEAVTIVATED AND AIRCRAFT RETURNED TO BASE UNPRESSURIZED AND TROUBLESHOT SYSTEMS INDICATING COLD AIR UNIT WAS AT FAULT. UNIT WAS REPLACED WITH SERVICEABLE PART. GROUND RUN PERFORMED WITH NO FAULT FOUND. AIRCRAFT RETURNED TO SERVICE. (TC# 20060706005)                                                            1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20060807000652006080700065EU  2006       8          7          CA060706006      120060706G32309740926112      RELAY                                   PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  HYD POWER       FAILED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            CLCLIMB          1                      CA       1055510555                                                     (CAN) LANDING GEAR WOULD NOT RETRACT FULLY AND HYDRAULIC LIGHT CAME ON AFTER LANDING GEAR WAS SELECTED UP IN CLIMB.  CREW CHECK HYDRAULIC CONTROL CB AND IT WAS IN.  CREW FOLLOWED CHECK LIST AND SELECTED GEAR DOWN AND HAND PUMPED LANDING GEAR DOWN AND LOCKED.  A/C WAS FLOWN TO MAINTENANCE BASE WITH GEAR DOWN AND LANDED WITHOUT INSIDENCE.  HYDRAULIC SYSTEM TROUBLESHOOTING CARRIED OUT AND HYDRAULIC POWER CONTROL RELAY K601 FOUND TO BE AT FAULT.  RELAY REPLACED AND LANDING GEAR/HYDRAULIC SYSTEMS FUNCTION CHECKED SERVICEABLE (TC# 20060706006)                                                                                                                                                                                 1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20060807000862006080700086WP  2006       8          7          CA060706007      120060705G291089H1014738LGD4  LINE                                    GRUMANTS2   TS2ACALFORST3951102WP  WRIGHTR1820 982C9HE2    67020EA  HAMSTD43D   43D51       NE  AT BEND         CHAFED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING ROUTINE MAINTENANCE IT WAS NOTED THAT THE RH MLG DOOR ACTUATOR OPEN LINE WAS FOUND CHAFED BEYOND LIMITS. THE LINE WAS CHAFED BY AN ADJACENT FLEX LINE. THE AFFECTED LINE WAS REPLACED AND A GEAR SWING WAS COMPLETED. THE AIRCRAFT WAS RETURNED TO SERVICE. (TC# 20060706007)                                                                                                                                                                                                                                                                                                                                                                                                                                                      2H72 4R4  R  A25WE   E259    6  CP8879    
20060807000942006080700094EA  2006       8          7          CA060706008      120060620G291366WA300         PUMP                                    CNDAIRCL215 CL2151A10   1900320EA  PWA   R2800 CA3         52026NE                              HYD SYSTEM      BROKEN          W      A   UNSCHED LANDING                                                                                 K  FLUID LOSS                                                                    APAPPROACH       1                      CA            579                                                       (CAN) AIRCRAFT SUFFERED HYDAULIC FAILURE. PERFORMED EMERGENCY GEAR EXTENSION AND LANDED SAFELY. HYDRAULIC LEAK FOUND ON ENGINE DRIVEN HYDRAULIC PUMP. THE END CAP FACEPLATE HAD A BROKEN BOLT AND THE BOLT IT WAS LOCKWIRED TO BESIDE IT HAD BACKED OFF. WITH BOTH BOLTS INEFFECTIVE, THE SEAL BLEW OUT BEHIND THE FACE PLATE AND ALL OF THE HYDRAULIC FLUID WAS PUMPED OVERBOARD. SUSPECTED PREVIOUS OVERTORQUING OF BOLT MAY HAVE CAUSED THE FAILURE (TC# 20060706008)                                                                                                                                                                                                                                                                        2H72 4R4  RRTA14EA   E231                 
20060922001062006092200106NM  2006       9          22         CA060707001      120060626G24972431154B10      WIRE                                    DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  TERMINAL END    BURNED          W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA                                                                      (CAN) CREW REPORTED ELECTRICAL ODOR FROM BEHIND F/O`S SEAT DURING FLIGHT. LASTED FOR APPROX 10 MINUTES. MAINTENANCE FOUND OVERHEATED WIRES, CB`S AND BUS BARS ON THE RT SECONDARY DC CB PANEL. SPECIFIC ITEMS REPLACED AS FOLLOWS, (IPC 24-50-00 FIG.10 PAGES 0 TO 6.  WIRE P/N 2431-154B10 FROM CB D1-RT FLARE LIGHT SECONDARY BUS REPLACED DUE TO ONE END OF WIRE AT TERMINAL END BADLY BURNED. APPEARS TO HAVE BEEN CAUSED BY ARCING OF THE WIRE.  WIRE MAY HAVE LOOSENED OVER TIME DUE TO VIBRATION AS THERE DOES NOT APPEAR TO HAVE BEEN ANY RECENT WORK COMPLETED IN THIS AREA.  WIRE P/N 2431-156A10 FROM CB C1-BUFFET POWER TO SECONDARY BUS LINK ON SECONDARY BUS BAR BETWEEN ROWS 4 AND 5 REPLACED DUE TO ONE END OF WIRE AT TERMINAL 2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060811000542006081100054NE  2006       8          11         CA060707002      220060626G73148187B           MOTOR           ROBSIN                  ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              FUEL PUMP       FAILED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      CA       987        110738                                              (CAN) PILOT WAS UNABLE TO USE THE ELECTRIC PUMP TO PRIME THE ENGINE.  TROUBLESHOOTING REVEALED THE PUMP WAS GETTING POWER.   FUEL PUMP ASSEMBLY WAS REPLACED, AND NO FURTHER DEFECTS FOUND. (TC NR 20060707002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1G71 3O3  O  H11NM   1E4                  
20060811000552006081100055CE  2006       8          11         CA060707005      120060704G553004310093        FITTING                                 CESSNA150   150M        2071830CE  CONT  O200  O200A       17020SO  MCAULY1A102 1A102OCM    GL  VERTICAL FIN    CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       8896                                                           (CAN) DURING 100 HOUR INSPECTION AME FOUND WHAT APPEARED TO BE A CRACK IN THE RADIUS OF THE LT FLANGE OF THE LT FITTING ATTACHING THE VERTICAL FIN TO THE HORIZONTAL STABILIZER.  WHEN THE PART WAS REMOVED FROM THE AIRCRAFT THE LT FLANGE WAS FOUND TO BE BENT TOWARDS THE RT FLANGE, AND WHEN MOVED AWAY FROM THE RT SIDE, IT BROKE FROM THE BASE OF THE FITTING REVEALING INTERGRANULAR CORROSION. (TC NR 20060707005)                                                                                                                                                                                                                                                                                                                      1H71 3O3  O  3A19    E252    5  NP918     
20060811000562006081100056EA  2006       8          11         CA060708001      120060624G2150GG670950099     ACM                                     CNDAIRCL600 CL6002C10   1390015EA                                                               RIGHT           FAILED          W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA       6557       00660                                               (CAN) CREW NOTED THAT THEY GOT RT PACK AUTO FAIL CAUTION AND THEN HAD A STRONG ELECTRICAL BURNNG SMELL /SMOKE IN REAR SECTION OF CABIN. THE PACK WAS REMOVE AND REPLACED IAW AMM.   PLEASE ADD THE MFG IN THE MANUFACTURER MENU.   THANK YOU  (TC  20060708001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F    RTA21EA                        
20060814001002006081400100SO  2006       8          14         CA060710002      120060707G3213MS28775335      SEAL                                    PIPER PA31  PA31350     7103110SO  LYC   O540  TIO540J2BD  41532EA  HARTZLHCE3Y HCE3YR2A    GL  MLG             CUT             W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) ON THE RAMP AFTER REFUELLING, PILOTS NOTED THE LT MLG OLEO WAS LEAKING FLUID AND DEFLATING. MAINTENANCE FOUND THE LT OLEO COMPLETELY DEFLATED AND APPROX. 1 LITRE OF HYDRAULIC FLUID ON THE RAMP UNDER THE LT OLEO. AFTER OLEO REMOVAL, FOUND THE LOWER OLEO BEARING INNER O-RING SEAL SPIRAL CUT APPROX. 1 INCH ALONG THE SEAL. REPLACED SEAL AND OLEO SERVICED BY AMO 128-94. (TC NR 20060710002)                                                                                                                                                                                                                                                                                                                                       1L72 3O3  O  A20SO   E14EA   5  CP33EA    
20060814001012006081400101SO  2006       8          14         CA060710003      220060707G7322S122210         THROTTLE CONTROL                        CESSNA206   U206B       2073322CE  CONT  O520  IO520D      17032SO                                              SEPARATED       W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       370                                                            (CAN) DURING A SCHEDULED 50 HOUR INSPECTION THE THROTTLE CONTROL WAS FOUND TO BE SEPARATED AT THE SWAGE AREA JUST AFTER THE CLAMP AREA ON THE ROD END END ALLOWING THE CONTROL GUIDE TO MOVE ALONG WITH THE CONTROL END POSSIBLY RESULTING IN CONTROL JAMMING. (TC NR 20060710003)                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O3  O  A4CE    E5CE                 
20060809001932006080900193EU  2006       8          9          CA060710005      120060622G6720350A75111720    SHIM                                    SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D         NE                              TAIL ROTOR      MISINSTALLED    W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A 100 HR INSPECTION OF AN A-STAR IN THE FIELD, THE ENGINEER PERFORMING THE INSPECTION FOUND THAT THE T/R SERVO FRICTION/GUIDE SHIM (PAD) WAS INSTALLED ON THE FORWARD BOLT AND NOT ON THE AFT ONE.  WHEN RT PEDAL IS APPLIED THE SERVO FRICTION/GUIDE SHIM (PAD) SLIDES .7500 PERCENT OF THE WAY OUT OF THE FIXED GUIDE TAILBOOM). THIS CONDITION COULD POTENTIALLY CAUSE THE SERVO TO JAM.   THE FRICTION/GUIDE SHIM (PAD) WAS RELOCATED THE THE AFT BOLT IAW THE MM AND THE SERVO WAS CHECKED FOR CORRECT OPERATION. (TC NR 20060710005)                                                                                                                                                                                         1G71 3U3  U  H9EU    E19EU                
20060809001942006080900194NE  2006       8          9          CA060710006      220060706G73203031829         LINE                                    AIRTRCAT802 AT802       0390305SW  PWA   PT6   PT6A67A     52043NE  HARTZLHCB5M HCB5MA3     GL  P3              CRACKED         W      O   OTHER                                                                                           R  PARTIAL RPM/PWR LOSS                                                          APAPPROACH       1                      CA       1748                                                           (CAN) DURING THE APPROACH TO THE AIRPORT, THE ENGINE LOST POWER. THE AIRCRAFT WAS DAMAGED ON LANDING. DURING PRELIMINARY INVESTIGATION, IT IS SUSPECTED THAT THE P3 LINE CRACKED CAUSING THE ENGINE TO GO INTO FLIGHT IDLE. THE ENGINE HAS BEEN REMOVED FROM THE AIRCRAFT AND HAS BEEN SHIPPED FOR FURTHER INVESTIGATION AND EVALUATION. UPON RECEIPT OF FINDINGS, WILL ADVISE. (TC NR 20060710006)                                                                                                                                                                                                                                                                                                                                             1L71 3T4  TNCA19SW   E26NE   6  CP44GL    
20060810000042006081000004NE  2006       8          10         CA060711001      220060711G7240                CASE                                                                       PWA   JD15  JT15D1A          NE                              GAS GENERATOR   CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) CRACKED GAS GENERATOR CASE WAS FOUND CRACKED AT THE LONGITUDINAL WELD AND CIRCUMFERENTIAL WELD.  SB7240 IS AVAILABLE AND WILL REPLACE THE GAS GENERATOR CASE WITH A CASE WITH NO LONGITUDINAL WELDS. (TC NR 20060711001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         4  F          E25EA                
20060810000052006081000005CE  2006       8          10         CA060711002      120060710G2497D4FF10316GA     WIRE            FORD                    CESSNA172   172M        2072418CE  LYC   O320  O320E2D     41508EA  MCAULY1C160 1C160DTM    GL  VOLT REGULATOR  BURNED          W      H   DEACTIVATE SYST/CIRCUITS                                                                        B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA       4088                                                           (CAN) WHILE ON A LOCAL VFR FLIGHT OVER, THE PILOT SMELLED FUMES AND SAW SMOKE COMING FROM BEHIND THE INSTRUMENT PANEL. THE PILOT ALSO NOTICED THAT THE HIGH VOLTAGE WARNING LIGHT WAS ON AND THE AMMETER SHOWING A DISCHARGE. THE PILOT REPORTED THE SITUATION TO THE FSS OPERATOR AND SUBSEQUENTLY TURNED OFF THE MASTER SWITCH, LANDING WITHOUT FURTHER INCIDENT. MAINTENANCE PERSONNEL DISCOVERED A BURNED WIRE FROM THE VOLTAGE REGULATOR TO THE HIGH VOLTAGE LIGHT. PARTS OF THE REGULATOR CIRCUIT BOARD SHOWED HEAT DAMAGE. THE VOLTAGE REGULATOR, HIGH VOLTAGE SENSOR HIGH VOLTAGE LIGHT AND BURNED WIRE WERE REPLACED. AIRCRAFT WAS RETURNED TO SERVICE WITHOUT FURTHER INCIDENT. (TC NR 20060711002)                                   1H71 3O3  ONT3A12    E274    5  NP910     
20060913002912006091300291NM  2006       9          13         CA060711003      120060711G24339498828VS20     TRU                                     DHAV  DHC8  DHC8102     2809003NM                                                               NR 1            FAILED          W      H   DEACTIVATE SYST/CIRCUITS                                                                        B  SMOKE/FUMES/ODORS/SPARKS                                                      ININSP/MAINT     1                      CA                                                                      (CAN) THE EVENT OCCURRED DURING C-CHECK PROCEDURE AT THE EXTERNAL POWER APPLICATION. THE NR 1 TRU START TO PRODUCE HEAVY SMOKE AND SOME COPPER PARTICLES IN FUSION. COPPER PARTICLES PRODUCE SOME BURNING  HOLES IN THE EXHAUST COOLING DUCT. THE NORMAL CAUTION LIGHT NEVER COME ON BEFORE THE ELECTRICAL POWER MANUALLY CUT OFF. (TC NR 20060711003)                                                                                                                                                                                                                                                                                                                                                                                          2H72 4T    RTA13NM                        
20060810000062006081000006EA  2006       8          10         CA060711004      220060710G7414                DISTRIBUTOR GEARCONT                    ROBSINR44   R44         7640120WP  LYC   O540  O540F1B5    41532EA                              MAGNETO         DAMAGED         W      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  APAPPROACH       1                      CA                  E01HA039R                                           (CAN) AC WAS ON FINAL APPROACH WHEN PILOT HEARD A CHANGE IN ENGINE NOISE FOLLOWED BY LOW ROTOR HORN. INITIATED AN AUTOROTATION, NOTICED THAT ENGINE, M/R RPM`S RETURNED TO NORMAL. CONTINUED HIS APPROACH AS INITIALLY PLANED, LANDED HELICOPTER WITHOUT FURTHER INCIDENT. ONCE ON GROUND,  PILOT DID A MAG CHECK WHEN LT MAGNETO WAS SELECTED, ENGINE QUIT. LT MAGNETO WAS REPLACED, AC RETURNED TO SERVICE. UPON REMOVAL OF MAGNETO, DISTRIBUTOR GEAR IN MAGNETO WAS FOUND TO HAVE SEVERAL TEETH WORN OR BROKEN OFF.  HAVE DECIDED TO HAVE MAGNETOS O/H EVERY 500 HRS. O/H WILL INCLUDE REPLACING DISTRIBUTOR GEAR, EVENTHOUGH MANUAL DOES NOT CALL FOR IT. (TC NR 20060711004)                                                               1G71 3O3  O  H11NM   E295                 
20060810000072006081000007EA  2006       8          10         CA060711005      220060706G8530SLC36005F       CYLINDER HEAD   LYC                     CESSNA172   172P        2072436CE  LYC   O320  O320D2J     41508EA  MCAULY1C160 1C160DTM    GL  ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1850       L1067229A                                           (CAN) THIS THE 3RD CYLINDER IN 100 HOURS IS CRACKED THE SAME AS THE PREVIOUS 2. CRACKED APPROXIMATLY 30 PERCENT AROUND THE CYLINDER HEAD. CRACKED FROM THE OUTER MOST EXHAUST FLANGE STUD ROUGHLY 2 OR 3 INCHES TO THE EXHAUST VALVE SEAT. THEN CRACK CONTINUING FROM 180 DEGREE ACROSS THE EXHAUST VALVE SEAT TO THE SPARK PLUG HOLE (TC NR 20060711005).                                                                                                                                                                                                                                                                                                                                                                                      1H71 3O3  ONT3A12    E274    5  NP910     
20060810000082006081000008EA  2006       8          10         CA060711006      220060706G8530SLC36005F       CYLINDER HEAD   LYC                     CESSNA172   172P        2072436CE  LYC   O320  O320D2J     41508EA  MCAULY1C160 1C160DTM    GL  ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1850       L1067239A                                           (CAN) THIS IS CYL NR 4 IN 100HRS. THE PREVIOUS 3 CYLINDERS EXHIBITED THE SAME TYPE AND LOCAL OF CRACKS. THIS CYLINDER HAS A ONE AND A HALF INCH LONG CRACK AT THE OUTER MOST EXHAUST FLANGE STUD MOVING TOWARDS THE EXHAUST VALVE SEAT. ALSO A CRACK BEGINNING AT THE EXHAUST VALVE SEAT AND MOVING TOWARDS THE SPARK PLUG HOLE (TC NR 20060711006)                                                                                                                                                                                                                                                                                                                                                                                             1H71 3O3  ONT3A12    E274    5  NP910     
20060810000092006081000009GL  2006       8          10         CA060711007      320060707G611005503214        BULKHEAD        CESSNA                  CESSNA172   172P        2072436CE  LYC   O320  O320D2J     41508EA  MCAULY1C160 1C160DTM    GL  SPINNER         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) THIS FORWARD SPINNER BULKHEAD HAS BEEN IN SERVICE WITH THE ORIGINAL (THIN MATERIAL) SPINNER. THE BULKHEAD HAS CRACKS TO 1.25 INCHES ACROSS EACH/ALL 6 PROP BOLK HOLES. (TC NR 20060711007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1H71 3O3  ONT3A12    E274    5  NP910     
20060810000102006081000010    2006       8          10         CA060711008      420060710G611305503214        BULKHEAD                                CESSNA172   172N        2072434CE  LYC   O320  O320D2J     41508EA  MCAULY1C160 1C160DTM    GL  SPINNER         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       489                                                            (CAN) THE SPINNER FORWARD BULKHEAD WAS INSTALLED NEW ONE YEAR EARLIER, WITH THE NEW HEAVIER MATERIAL SPINNER IAW SNL03-9 (ALTERNATE PROPELLER SPINNER INSTALATION) THE FWD BULKHEAD HAS CRACKS OF APPROXIMATLY 1.5 INCHES EACH  COMING ACROSS EACH PROP BOLT HOLE AT THE TOP OF AND JUST OUTSIDE OF THE BOLT WASHER CONTACT AREA, BUT NOT DIRECTLY INTERFACING WITH THE HOLE ITSELF. (TC NR 20060711008)                                                                                                                                                                                                                                                                                                                                        1H71 3O3  ONT3A12    E274    5  NP910     
20060810000112006081000011EA  2006       8          10         CA060712000      120060501G5610NP13932114      WINDOW                                  CNDAIRCL600 CL6002C10   1390015EA                                                               COCKPIT         FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA       1436                                                           (CAN) THE RT SIDE WINDOW SHATTERED IN FLIGHT AT FL320, OUTTER SECTION. WINDOW IS POST SB (TC NR 20060712000)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F    RTA21EA                        
20060810000122006081000012SW  2006       8          10         CA060712001      120060710G6220407310101101    BEARING         BELL                    BELL  407   407         1182206SW  ALLSN 250C  250C47B          GL                              MAIN ROTOR      SEPARATED       W      A   UNSCHED LANDING                                                                                 E  VIBRATION/BUFFET                                                              NRNOT REPORTED   1                      CA       5644       A141                                                (CAN) AIRCRAFT DEVELOPED A VERTICIAL VIBRATION, VISUAL INSPECTION REVEALED A SEPERATED SHEAR BEARING. (TC NR 20060712001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1G71 3U3  UO H2SW    E1GL                 
20060811000572006081100057SO  2006       8          11         CA060712002      120060704G27201582102         TUBE                                    PIPER PA23  PA23250     7102308SO  LYC   O540  IO540C4B5   41532EA  HARTZLHCE2Y HCE2YR2     GL  RUDDER          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       10678                                                          (CAN) DUE TO HIGH WINDS THAT HIT THE RUDDER (WITHOUT CONTROL LOCKS INSTALLED) INSTALLED THE AIRCRAFT FOR DAMAGE. THE RUDDER PEDAL TUBE WAS FOUND CRACKED. THE PART WAS REPLACED. (TC NR 20060712002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L72 3O3  O  1A10    1E4     5  CP9EA     
20060811000582006081100058EA  2006       8          11         CA060712003      120060702G2497WIRE2XA80ABBLU  FEEDER CABLE                            CNDAIRCL601 CL6013A     8070802EA  GE    CF34  CF343A      30015NE                              FS 625.30       ARCED           W      O   OTHER                                                                                           J  WARNING INDICATION                                                            APAPPROACH       1                      CA       6869                                                           (CAN) RT GEN TRIPPED OFFLINE DURING APPROACH. GEN OFF ANNUNCIATOR CAME ON, PWR AUTO TRANSFERED FROM GEN 1. NO LOSS OF PWR ON ANY AC BUSES. AC FERRIED WITH GENERATOR 2 SELECTED OFF. ON 3RD ENGINE RUN, PROBLEM WAS DUPLICATED. PROBLEM WAS ISOLATED TO A WIRING PROBLEM. MAIN GEN FEED WIRES AWG 8 WERE INSPECTED. AT FS 625.30 JUST AFT OF AFT PRESURE BULKHEAD, EVIDENCE OF ARCING FROM FEEDER WIRE TO AC STRUCTURE WAS FOUND. ARCING REMOVED APPROX 0.780 SQUARE INCH OF MATERIAL. PROBLEM APPEARED TO BE INCORRECT INSTALLATION OF FEEDER WIRES DURING ORIGINAL AC BUILD. INADEQUATE CLEARANCE BETWEEN WIRING AND STRUCTURE. OPPOSITE SIDE WAS INSPECTED AND FOUND WIRING HAD A SAFE CLEARANCE TO STRUCTURE.  (TC NR 20060712003)          2L72 4F4  FRTA21EA   E15NE                
20060810000132006081000013EA  2006       8          10         CA060712004      220060706G8530A4871           RETAINER                                ROBSINR22   R22BETA     7640110NM  LYC   O320  O320B2C     41508EA                              NR2 CYL BAFFLE  BROKEN          W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) NR 2 AND NR 4 CYLINDER LOWER BAFFLE IB RETAINER BROKE CAUSING BAFFLE CONTACTING  NR 2 CYLINDER`S OIL RETURN LINE THUS CHAFED OIL LINE AND OIL SEEPAGE EVIDENT DURING DAILY CHECK.  NR 2 AND NR 4 CYLINDER BAFFLE RETAINER  P/N A4871  (TC NR 20060712004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1G71 3O3  O  H10WE   E274                 
20060814000592006081400059EA  2006       8          14         CA060712005      220060704G72003031300         ENGINE                                  DHAV  DHC7  DHC7103     2802710EA  PWA   PT6   PT6A50      52043EA  HAMSTD24PF  24PF305     GL  NR 3            FAILED          W      A   UNSCHED LANDING                                                                                 BJ SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION                                  CLCLIMB          1                      CA       119364012                          86585                       (CAN) ABORTED TAKEOFF DUE TO NR 3 ENGINE FAILURE. DURING TAKEOFF ROLL AIRCRAFT REACHED APPROXIMATELY 45 KNOTS WHEN A JOLT WAS FELT. THE PILOT NOTICED ABNORMAL READINGS ON THE NR 3 ENGINE GAUGES & LARGE AMOUNTS OF SMOKE COMING OUT OF THE NR 3 ENGINE. EMERGENCY SHUT DOWN INCLUDING ACTIVATION OF NR 3 FIRE BOTTLE. THE AIRCRAFT CAME TO A SUCCESSFUL HALT ON THE RUNWAY. UPON ARRIVING AT THE SIGHT OF THE INCIDENT & NOTICED OIL HAD BLOWN OUT THROUGH BOTH OF THE OPENINGS FROM THE BLEED AIR VALVES. INSPECTION REVEALED THAT THE COMPRESSOR HAD FAILED AND THROWN ONE BLADE. AS THE BLADE EXITED THE COMPRESSOR INTAKE IT RUPTURED ONE OF THE OIL TRANSFER TUBES ON THE RIGHT HAND SIDE OF THE ENGINE AND LARGE AMOUNT OF OIL CAME THRO2H74 4T4  T  A20EA   E4EA    6  CP1NE     
20060810000142006081000014CE  2006       8          10         CA060712006      120060707G324695442077        WHEEL                                   CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              NLG             CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) AFTER ONLY ONE TIRE CHANGE AND 9 MONTHS IN SERVICE THE NOSE WHEEL WAS REMOVED AND FOUND EXCESSIVE CORROSION THE BOLT HOLES AND SURFACE CORROSION ON THE INNER WHEEL HALVES. (TC NR20060712006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L72 4F4  F  A22CE   E1NE                 
             20081104     SW  2008       11         4          CA060712007      120060710G6320212040054007    CASE                                    BELL  212   212         1181420SW                                                               M/R TRANSMISSIONCRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            234                                                       (CAN)  THE CRACKED SUPPORT CASE AT THE LIFT LINK FITTING. (TC NR 20060712007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1G71 4U      H4SW                         
20060913002942006091300294CE  2006       9          13         CA060712008      120060706G5310504200337       SUPPORT BEAM                            BEECH 100   A100        1152915CE  PWA   PT6   PT6A28           EA                              FUSELAGE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) UNDER THE PILOTS FLOOR BOARDS AT FLIGHT STATION 107 THE PILOTS RUDDER QUADRANT SUPPORT BEAM WAS FOUND CRACKED. THESE CRACKS WERE FOUND AT (2) OF THE (4) NUT PLATES. WE HAVE FOUND THESE SAME CRACKS ON 4 OTHER OF OUR AIRCRAFT AROUND THE SAME LOCATIONS. THE BEAM WAS REPLACED. (TC NR 20060712008)                                                                                                                                                                                                                                                                                                                                                                                                                                     1L72 3T4  T  A14CE   E4EA                 
20060913002962006091300296WP  2006       9          13         CA060712009      120060711G6310NAS4283A12      BOLT            ROBSIN                  ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              CLUTCH ACTUATOR BENT            W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       36         3172                                                (CAN) A/C TAFT 36.5 HOURS.   MAIN BELT TENSION WAS TO BE ADJUSTED, WHEN IT WAS FOUND THAT THE ADJUSTMENT BOLT, ON THE CLUTCH ACTUATOR, COULD NOT BE MOVED.  THE BOLT IS USUALLY HELD IN PLACE WITH A BACK UP NUT.  THE BACK UP NUT WAS IN PLACE, AND MOVED AS NORMAL.  THE HEAD OF THE BOLT, USED TO STOP A MICRO SWITCH, WAS TIGHT UP AGAINST THE FLANGE. VARIOUS ATTEMPTS WERE MADE TO MOVE THE BOLT, UNTIL FINALLY THE ASSEMBLY WAS REMOVED FROM THE AIRCRAFT WHERE IT COULD BE MOVED, STILL WITH SOME DIFFICULTY.  THE BOLT WAS REPLACED WITH A SERVICEABLE PART, AND THE CLUTCH ACTUATOR WAS REINSTALLED.  NO OTHER DEFECTS WERE NOTED.  (TC NR 20060712009)                                                                               1G71 3O3  O  H11NM   1E4                  
20060810000152006081000015NE  2006       8          10         CA060713003      220060703G8530327628          CYLINDER                                CNDAIRCL215 CL2151A10   1900320EA  PWA   R2800 R2800CA3    52026NE  HAMSTD43E   43E60       NE  ENGINE          CRACKED         W      A   UNSCHED LANDING                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      CLCLIMB          1                      CA                                                                      (CAN) ON CLIMB AFTER SCOOP PILOT NOTICED FLICKER IN THE MANIFOLD PRESSURE GAUGE. ANOTHER A/C ADVISED PILOT OF A SMOKE TRAIL. THE LOAD WAS PITCHED AND THE A/C WAS RETURNING WHEN ANOTHER A/C CONFIRMED THE SMOKE BUT NO FIRE. THE A/C RETURNED TO BASE AND A CRACKED CYLINDER WAS FOUND AND CHANGED. THE A/C WAS RETURED TO SERVICE. (TC NR 20060713003)                                                                                                                                                                                                                                                                                                                                                                                        2H72 4R4  RRTA14EA   5E8     6  CP871     
20060811000592006081100059EA  2006       8          11         CA060713004      120060711G281021564075        FUEL CELL                               CNDAIRCL215 CL2156B11215       EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  LT WING         LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       1384                                                           (CAN) AC 2032 DEVELOPED A FUEL LEAK IN THE LT WING ON JULY 10/2006.  ALL LT FUEL CELLS WERE REMOVED AND TESTED. CELLS NR 8 PT NR 215-64075, NR 6 PT NR 215-64002-2, NR 4 PT NR 215-64002-4, NR 3 PT NR 215-64006-6 WERE FOUND TO BE LEAKING UPON TESTING. LEAKING CELLS WERE REPLACED. (TC NR 20060713004)                                                                                                                                                                                                                                                                                                                                                                                                                                      2H72 4T4  TRTA14EA   E20NE   6  CP7NE     
20060810000162006081000016NE  2006       8          10         CA060714001      220060705G7261793651          LINE                                    BOEING727   727223      1384074NM  PWA   JT8   JT8D15      52051NE                              ENGINE OIL SYS  LOOSE           W      E   ENGINE SHUTDOWN                                                                                 WKJINADEQUATE Q C            FLUID LOSS                WARNING INDICATION        CRCRUISE         1                      CA                                                                      (CAN) CREW OBSERVED LOSS OF OIL QUANTITY NR 1 ENGINE. ENGINE SHUTDOWN PRIOR TO LOW OIL PRESSURE WARNING LIGHT ILLUMINATING. MAINTENANCE DETERMINED UPON THE JUST COMPLETED NR6 OIL BEARING REPLACEMENT THE FORWARD END OF THE PRESSURE TUBE WAS NOT SECURED AND LOCK WIRED CAUSING LEAK. LINE SECURED AND LEAK CHECK CARRIED OUT SERVICEABLE. (TC NR 20060714001)                                                                                                                                                                                                                                                                                                                                                                               2L73 4F4  F  A3WE    E2EA                 
20060810000172006081000017SW  2006       8          10         CA060714002      120060605G2121EM6081          BLOWER                                  GULSTM690TP 690D        3970405SW  GARRTTTPE331TPE3315     01514WP  ROTOL R306  R306382F7   GL  CABIN           BURNED          W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      DEDESCENT        1                      CA            2624                                                      (CAN) DURING DESCENT FLIGHT CREW NOTED A STRONG ODOR FROM THE HEATER OUTLETS. CREW SELECTED RECIRCULATION BLOWER SWITCH OFF AND LANDED AIRCRAFT. GROUND OPERATION CHECK OF THE ENVIRO SYSTEM FOUND RT RECIRCULATION BLOWER INOPERATIVE. FURTHER INSPECTION OF THE BLOWER ASSEMBLY FOUND SIGNS OF MOTOR OVERHEATING AND ROUGHNESS. BLOWER ASSEMBLY REPLACED WITH OVERHAULED ITEM. RECIRCULATION BLOWER NOT IN MAINTENANCE LIMITS SCHEDULE. PART IS ON CONDITION. (TC NR 20060714002)                                                                                                                                                                                                                                                             1H72 3T4  T  2A4     E4WE    6  CP8EU     
20060810000182006081000018SW  2006       8          10         CA060714003      120060704G30103D249503        TIMER                                   GULSTM690TP 690D        3970405SW  GARRTTTPE331TPE3315     01514WP  ROTOL R306  R306382F7   GL  DEICE SYSTEM    FAILED          W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB FLIGHT CREW NOTED VISUALLYTHAT WING DE-ICER BOOTS WERE INFLATED AND WOULD NOT DEFLATE. FLIGHT CREW SELECTED BLEED AIR CLOSED RESULTING IN BOOTS DEFLATING AND RETURNED TO DEPARTURE BASE.  MAINTENANCE FOUND THE DE-ICE TIMER TO BE CAUSE OF FAULT. TIMER REPLACED WITH OVERHAULED ITEM AND SYSTEM CHECKED OKAY. (TC 20060714003)                                                                                                                                                                                                                                                                                                                                                                                            1H72 3T4  T  2A4     E4WE    6  CP8EU     
20060810000192006081000019    2006       8          10         CA060714007      420060713G6113C35325P         SUPPORT         HARTZL                  CESSNA206   U206F       2073333CE  CONT  O520  IO520F      17032SO                              SPINNER         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       392        AC6880                                              (CAN) DURING 100 HR INSP REMOVED SPINNER AND FOUND THE INNER SUPPORT CRACKED. (TC NR 20060714007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1H71 3O3  O  A4CE    E5CE                 
20060913003132006091300313CE  2006       9          13         CA060716001      120060714G571207221991        RIB                                     CESSNA185   185D        2072812CE  CONT  O470  IO470F      17026SO  MCAULY2A34C D2A34C58    GL  WING            CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3981 3981                                                      (CAN) WING CENTER RIBS AT STATION 190.0 IN BOTH WINGS WERE FOUND CRACKED AT THE TRAILING EDGE WERE THEY ATTACH TO THE AUX REAR SPAR OF THE WING. STN 190.0 IN THE OB AILERON HINGE ATTACH POINT. IT IS SUSPECTED THAT AT SOME TIME THIS AIRCRAFT WAS SUBJECTED TO WING GUSTS WITHOUT THE CONTROLS LOCKED.  SEE ATTACHED PHOTO`S OF THE CRACKED RIBS. (TC NR 20060716001)                                                                                                                                                                                                                                                                                                                                                                        1H71 3O3  O  3A24    3E1     5  CP3EA     
20060808000882006080800088NE  2006       8          8          CA060717001      220060701G853011876           PUSHROD                                 AYRES S2    S2RHGT65    0970110SO  PWA   R1340 AWASP       52016NE  HAMSTD12D   12D40       NE  ENGINE          LOOSE           W      A   UNSCHED LANDING                                                                                 RYJPARTIAL RPM/PWR LOSS      ENGINE STOPPAGE           WARNING INDICATION        CLCLIMB          1                      CA                                                                      (CAN) THE BALL END ON THE NR 5 EXHAUST VALVE PUSHROD WAS LOOSE. THIS CAUSED THE PUSHROD TO LENGTHEN REMOVING ANY VALVE CLEARANCE. THIS CAUSED AN OPEN EXHAUST VALVE SITUATION WHICH ALLOWED EXHAUST FLAME TO ENTER THE NR 5 CYLINDER. WHEN THE NR 5 INTAKE VALVE OPENED THIS ALLOWED THE FLAME TO BURN THE AIR/FUEL MIXTURE THROUGHOUT THE ENTIRE BLOWER AND MANIFOLD CAUSING THE ENGINE TO LOSE POWER AND THEN STOP. (TC NR 20060717001)                                                                                                                                                                                                                                                                                                       1L71 3T3  RNC        ATC14   5  CP257     
20060808000902006080800090CE  2006       8          8          CA060717002      120060710G782005501579        HEATER                                  CESSNA172   172         2072402CE  CONT  O300  O300A       17022SO  MCAULY1A170 1A170DM     GL  MUFFLER         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       5791                               14566D9A                    (CAN) LT MUFFLER CRACKING, BURNING THROUGH. RT MUFFLER CRACKED. STACK CRACKED.  NOTE: CRACKS NOT VISIBLE WITH ATTACHMENTS (SCROUNDS) ON.  MUFFLER HEATER - LT P/N 0550157-9, RT P/N 0550157-32 (TC NR 20060717002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O3  ONT3A12    E253    5  NP857     
20060809001952006080900195CE  2006       8          9          CA060717003      120060706G7120075100331       MOUNT                                   CESSNA185   A185F       2072821CE  CONT  O520  IO520D      17032SO  MCAULY2A34C D2A34C58    GL  ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            44                                                        (CAN) DURING ROUTINE INSPECTION, IT WAS DISCOVERED THAT THE FWD LT MOUNT PAD WAS CRACKED. THIS ENGINE MOUNT WAS INSTALLED 44.8 HRS AGO. REPLACED ENGINE MOUNT WITH SERVICEABLE P/N 075-1003-31, AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060717003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1H71 3O3  O  3A24    E5CE    5  CP3EA     
20060926000752006092600075NM  2006       9          26         CA060717004      120060714G3231478441          SPRING                                  BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  NLG DOOR        BROKEN          W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) OPERATOR FOUND SPRING OF ALTERNATE NLG RELEASE BROKEN AT THE LOWER END. NEW SPRING INSTALLED. FLEET INSPECTION SCHEDULED. (TC NR 20060717004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
20060811000602006081100060EA  2006       8          11         CA060717005      120060715G5610NP1393229       WINDOW                                  CNDAIRCL600 CL600*             EA  GE    CF34  CF348C1          NE                              COCKPIT         FAILED          W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA                                                                      (CAN) CAPTAIN SIDE FLIGHT DECK WINDOW OUTSIDE PANE SHATTERED ON TAKEOFF. A/C RETURNED. 721377 HAVE INSPECTED THE A/C AND FOUND TO BE SAFE FOR FERRY FLIGHT WITH ZERO STOPS IAW THE RESTRICTIONS CONTAINED IN THE ATTACHED FLIGHT PERMIT. CAPT. SIDE WINDOW REPLACED, WINDOW HEAT AND PRESSURIZATION LEAK CHECKS COMPLETED AND CHECKED SERVICEABLE. (TC NR 20060717005)                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA21EA   EOOO63EN             
20060926000792006092600079WP  2006       9          26         CA060717006      120060715G6220369A7010        LOCK                                    HUGHES369   369A        4470503WP  ALLSN 250C  250C20B     03013GL                              MAIN ROTOR      UNSERVICEABLE   W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             CRCRUISE         1                      CA                                                                      (CAN) PILOT NOTICED FEEDBACK THRU CYCLIC CONTROL FROM MAIN ROTOR HEAD.  HELICOPTER WAS LANDED AT MAIN BASE AND SERVICEABLE UNLOCK WAS INSTALLED TSO 00.0 AND TESTED SATISFACTORY.   UNSERVICEABLE UNILOCK WILL BE SENT IN FOR OVERHAUL WITH A TEARDOWN REPORT REQUESTED (TC NR 20060717006)                                                                                                                                                                                                                                                                                                                                                                                                                                                     1G71 3U3  U  H3WE    E4CE                 
20060926001352006092600135EA  2006       9          26         CA060717007      120060703G3320BAO80061        BALLAST                                 DHAV  DHC7  DHC7*              EA  PWA   PT6   PT6A50      52043EA                              CABINLIGHTS     OVERHEATED      W      O   OTHER                                                                                           BM SMOKE/FUMES/ODORS/SPARKS  OVER TEMP                                           ININSP/MAINT     1                      CA                                                                      (CAN) VP-FBQ (DASH 7, S/NO 111) FLUORESCENT TUBE LAMP HOLDER OVERHEATING PROBLEM  SHORTLY AFTER RE-INSTATING POWER DURING A C CHECK, A STRONG SMELL OF BURNING WAS NOTED IN THE FWD SECTION OF THE AIRCRAFT. THE FAULT WAS TRACED TO A LAMP HOLDER AT THE FRONT OF THE CABIN IN THE OVERHEAD LIGHTING SYSTEM. THE LAMP HOLDER HAD SUFFERED SERIOUS OVERHEATING RESULTING IN THE MELTING OF THE CONTACTS WITH ASSOCIATED HEAT DAMAGE TO THE INSULATED PORTION OF THE HOLDER. THE FLUORESCENT TUBE HAD ALSO SUFFERED DAMAGE TO THE CONTACT PINS. THE FLUORESCENT TUBE HAD NOT BEEN DISTURBED DURING MAINTENANCE THE LIGHTING CIRCUIT BREAKERS HAD NOT TRIPPED. THE BALLAST UNIT PART NR IS BA08006-1. THE AIRCRAFT IS FITTED WITH A MIXTURE OF BA02H74 4T4  TRTA20EA   E4EA                 
20060926001362006092600136WP  2006       9          26         CA060717008      120060709G5630369350542       WINDOW                                  HUGHES369   369D        4470706WP  ALLSN 250C  250C20B     03013GL                              DOOR            DETACHED        W      O   OTHER                                                                                           D  INFLIGHT SEPARATION                                                           CLCLIMB          1                      CA                                                                      (CAN) HELICOPTER WAS CLIMBING OUT AT 70 KTS WHEN THE RT FWD DOOR WINDOW IMPLODED INTO THE CABIN.  UPON INVESTIGATION IT WAS FOUND THE WINDOW INSTALLED REQUIRED A RUBBER GASKET TO HOLD IT IN. THINKING IT WAS A MD WINDOW IT WAS INSTALLED WITH THE ORIGINAL FRAME. THE WINDOW THAT USES THE GASKET IS ABOUT .25 SMALLER IN DIAMETER ALLOWING IT TO COME OUT OF THE FRAME INTO THE CABIN.  A NEW WINDOW WITH A RUBBER GASKET WAS INSTALLED AND STAYED IN SATISFACTORY. (TC NR 20060717008)                                                                                                                                                                                                                                                     1G71 3U3  U  H3WE    E4CE                 
20060926001372006092600137NM  2006       9          26         CA060718001      120060714G29136617303         PUMP                                    BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  HYD SYSTEM      SPLIT           W      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) NR1 EDP FAILED DURING FLIGHT CAUSING NR1 HYDRAULIC SYSTEM DEPLETION. EMERGENCY CHECKLIST PERFORMED. UNEVENTFUL LANDING AND A/C STOPPED ON RWY AND LATER TOWED TO PARKING POSITION. PUMP HOUSING FOUND SPLIT. EDP REPLACED. GROUND RUNS AND LEAK CHECK CARRIED SERVICEABLE. A/C HAS BEEN RTS. (TC NR 20060718001)                                                                                                                                                                                                                                                                                                                                                                                                                          2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
20060811000612006081100061NE  2006       8          11         CA060718002      320060714G6110C459            THRUST PLATE    HARTZL      HCE4N3G     BEECH 200   200BEECH    1152920CE  PWA   PT6   PT642A           NE  HARTZLHCE4N HCE4N3      NE  PROPELLER       DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       435        HH278                               HH278           (CAN) UPON DISASSEMBLY OF THE PROPELLER, IT WAS FOUND TO HAVE A BROKEN THRUST PLATE SCREW (PN A3204). THE THRUST PLATE SCREW WAS FOUND JAMMED BETWEEN THE THRUST PLATE AND THE BLADE BUTT. AS A RESULT OF THIS BROKEN SCREW IT ALSO DAMAGED THE BETA PICKUP PLATE (PN C459) AND GOUGED THE BETA ROD (PN C453).  THE THRUST PLATE, BETA PICKUP PLATE, BETA ROD, ALL FOUR THRUST PLATE SCREWS, ALL SEALS, LUBRICANTS AND HUB NUTS WERE REPLACED, PROPELLER WAS ASSEMBLED, LOCKED AND THE PROPELLER RETURNED TO CUSTOMER. (TC NR 20060718002)                                                                                                                                                                                                      1L72 4T4  T  A24CE   E4EA    5  CP10NE    
20061213001352006121300135WP  2006       12         13         CA060718003      120060717G6510C0411           BEARING RACE    ROBSIN                  ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              TAIL ROTOR      ROUGH           W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       36         1326                                                (CAN) IT WAS NOTICED THAT THE DAMPER BEARING HAD TURNED ON THE TAIL ROTOR DRIVE SHAFT.  SLIPPAGE MARKS WERE ABOUT .5 INCH APART.  THE BEARING WAS REMOVED SO IT COULD BE INSPECTED, AND POSSIBLY REINSTALLED.   THE BEARING WAS FOUND TO BE ROUGH.  IT WAS ALSO NOTED THAT THE GREASE IN THE BEARING WAS A DIFFERENT COLOR THAN THE GREASE IN THE SAME BEARING IN OTHER AIRCRAFT, AND PARTS IN STORES.   THE BONDED PLATES WERE THE BEARING SITS WERE MEASURED AND FOUND TO HAVE A TOTAL INDICATED RUNOUT OF .0045 INCH.  MANUFACTURES LIMIT IS .003 INCH.   THE TAIL ROTOR DRIVE SHAFT ASSEMBLY IS TO BE REPLACED WITH A NEW UNIT. (TC NR 20060718003)                                                                                         1G71 3O3  O  H11NM   1E4                  
20060926001402006092600140EA  2006       9          26         CA060719001      220060714G73228198007         METERING UNIT                           BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  NR 1 ENG FUEL   SHEARED         W      A   UNSCHED LANDING                                                                                 Y  ENGINE STOPPAGE                                                               CRCRUISE         1                      CA       6117                                                           (CAN) DURING CRUISE THE PILOT FELT A YAW-MOMENT AT THE SAME TIME THE TRQ NR 1 WENT TO 0 PERCENT, POWERPLANT MESSAGE APPEARED, ENG NR 1 PROP RPM DOWN TO 600 RPM, ENG NO.1 ITT APP. 200 DEGREES C LESS THAN ENG NR 2. PILOT CONTINUED WITH HIS CHECK LIST, MANUAL FEATHERED PROP NR 1 AND MANUAL SHUTDOWN THE ENG NR 1. AIRCRAFT LANDED SAFELY WITH SINGLE ENGINE OPS. CDS FAULT READ OUT PERFORMED AND FOLLOWING CODES ARE STORED: 360, 907, 911, 935. FAULT CODES SUPPLIED SEEM TO INDICATE A FUEL STARVATION FROM THE FMU. FOUND FMU SHAFT SHEARED.  FMU TO BE REPLACED. (TC NR 20060719001)                                                                                                                                                  2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
20060814000602006081400060EU  2006       8          14         CA060719002      120060717G32339693001105      ACTUATOR                                PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  MLG             LEAKING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            153                                                       (CAN) ORIGINAL MAIN LANDING GEAR ACTUATOR REPLACED WITH AN OVERHAULED UNIT.  (ORIGINAL ACTUATOR HAD AN INTERNAL LEAK) HYDRAULIC SYSTEM FLUSHED BEFORE OVERHAULED ACTUATOR WAS INSTALLED. INTERNAL LEAK DEVELOPED IN TSO 153.3. HYDRAULIC SYSTEM FLUSHED AGAIN AND A REPAIRED ACTUATOR INSTALLED. NO CONTAMINATION NOTED IN FLUID AFTER EACH SYSTEM FLUSH.  HYDRAULIC SYSTEM LEAK CHECKED SERVICEABLE (TC NR 20060719002)                                                                                                                                                                                                                                                                                                                        1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20060814000612006081400061CE  2006       8          14         CA060719003      120060718G27107020362         POTENTIOMETER                           CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              ELEVATOR        SEPARATED       W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       7418                                                           (CAN) VISUAL INSPECTION CARRIED OUT ON ELEVATOR FDR SYSTEM DUE TO A FAILURE OF THE FDR CORRELATION FLIGHT TEST. FLIGHT TEST RECORDER SHOWED ELAVATOR SYSTEM NO RESPONSE TO SIGNAL. VISUAL INSPECTION REVEALED FAILED POTENTIOMETER SHAFT. REPLACED WITH NEW PART IAW MM. FLIGHT TEST TO BE CONDUCTED (TC NR 20060719003)                                                                                                                                                                                                                                                                                                                                                                                                                        1L72 4F4  F  A22CE   E1NE                 
20060926001482006092600148EU  2006       9          26         CA060719005      120060719G3246300720          WHEEL                                   BAG   JETSTMJETSTM3212  1500217EU  GARRTTTPE331TPE33110UG  01514WP  MCAULY4HFR344HFR34C652  NE  MLG             DAMAGED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) DURING TOWING OF AIRCRAFT THE PIC AND GROUND HANDLERS NOTICED A WOBBLE ON THE RH MLG. MAINTENANCE WAS CONTACTED AND IT WAS DISCOVERED THAT A 10" PIECE OF THE EDGE OF THE INNER WHEEL RIM WAS MISSING. THE TIRE STILL REMAINED INFLATED. THE WHEEL AND TIRE WAS REMOVED AND REPLACED WITH A SERVICEABLE UNIT. THE IMMEDIATE ADJACENT AREA WAS INSPECTED FOR SECONDARY DAMAGE, NONE OBSERVED.   (TC# 20060719005)                                                                                                                                                                                                                                                                                                                          2L72 4T4  TRTBA15CAA E4WE    6  C3PNE     
20060814000622006081400062SO  2006       8          14         CA060720001      120060621G55244A314003        ATTACH BRACKET                          EMB   110   EMB110P1    3260122SO  PWA   PT6   PT6A34      52043EA  HARTZLHCB3T HCB3TN3     GL  ELEVATOR        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING ROUTINE MAINTENANCE 2 CRACKS WERE DISCOVERED ON THE RT OB ELEVATOR HINGE ATTACH BRACKET. THE CRACKS WERE LOCATED ON THE LOWER FORWARD PORTION OF THE BRACKET IN THE MOST FORWARD PORTION OF A 90 DEGREE BEND AND WERE APPROX .7500 OF AN INCH IN LENGTH EACH. THE BRACKET WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060720001)                                                                                                                                                                                                                                                                                                                                                                               1L72 4T4  T  A21SO   E4EA    6  CP15EA    
20060926001492006092600149SO  2006       9          26         CA060720002      120060720G54114A27122201      CHANNEL                                 EMB   110   EMB110P1    3260122SO  PWA   PT6   PT6A34      52043EA  HARTZLHCB3T HCB3TN3     GL  RT NACELLE      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) WHILE CARRYING OUT MAINTENANCE IN THE RT LANDING GEAR AREA, A CRACK WAS FOUND IN THE IB LOWER NACELLE CHANNEL. THIS NACELLE CHANNEL IS THE ATTACH POINT FOR THE INBOARD  GEAR DOOR HINGE. THE CRACK WAS LOCATED IN AFT PORTION OF THE HINGE ATTACH AREA MEASURING APPROXIMATELY 3.5 INCHES IN LENGTH. THE CRACK WAS DIFFICULT TO SPOT DUE TO THE OBSTRUCTION CAUSE BY THE GEAR DOOR HINGE WHEN IT IS INSTALLED. THE NACELLE CHANNEL HAS BEEN REPLACED. (TC NR 20060720002)                                                                                                                                                                                                                                                                1L72 4T4  T  A21SO   E4EA    6  CP15EA    
20060926001522006092600152NM  2006       9          26         CA060723001      120060717G5311654653120       FRAME                                   BOEING737   737400      138449ANM                                                               BS 500B S28R-25LCORRODED        W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) FWD CARGO PIT FRAME TO SKIN AT BS 500B CORRODED BETWEEN STR 28R AND 28L (TC NR 20060723001).                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F    RTA16WE                        
20060926001532006092600153NM  2006       9          26         CA060723002      120060717G5311654653170       FRAME                                   BOEING737   737400      138449ANM                                                               BS 500C S27-28R CORRODED        W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) FWD CARGO PIT FRAME TO SKIN AT BS500C CORRODED STR 27R TO 28R (TC NR 20060723002).                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F    RTA16WE                        
20060926001562006092600156NM  2006       9          26         CA060723003      120060717G5311654653170       FRAME                                   BOEING737   737400      138449ANM                                                               BS 500C S28R-28LCORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) FWD CARGO PIT FRAME CORRODED AT BS 500C AND STR 28R TO 28L (TC NR 20060723003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F    RTA16WE                        
20060926001572006092600157NM  2006       9          26         CA060723004      120060717G53116546534         FRAME                                   BOEING737   737400      138449ANM                                                               BS 520 S27-28R  CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) SKIN TO FRAME ATTACH ANGLE CORRODED NR BS 520, STR 27R TO 28R (TC NR20060723004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA16WE                        
20060926001602006092600160NM  2006       9          26         CA060724001      120060713G2740MS28775232      O-RING                                  BOEING727   727225      1384077NM  PWA   JT8   JT8D15      52051NE                              STABILIZER      SWOLLEN         W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             DEDESCENT        1                      CA       1540915409                                                     (CAN) ON DESCENT STABILIZER OUT OF TRIM LIGHT ILLUMINATED, STABILIZER WOULD NOT RESPOND TO COMMANDS FROM AUTOPILOT, MAIN ELECTRIC TRIM OR MANUAL TRIM. FLIGHT CREW ACCOMPLISHED THE STABILIZER JAM EMERGENCY CHECK LIST AND LANDED UNEVENTFULLY. UPON INSPECT MAINTENANCE FOUND WATER INGRESSION IN THE GEAR BOX AND BRAKE ASSEMBLY DUE TO DAMAGED O-RINGS. STABILIZER GEAR BOX ASSEMBLY REPLACED IN ACCORDANCE WITH AMM 27-40-41. CONTRIBUTING FACTOR - EXCESSIVE RAIN EXPERIENCED DURING THE GROUND LAYOVER. (TC NR 20060724001)                                                                                                                                                                                                              2L73 4F4  F  A3WE    E2EA                 
20060926001622006092600162NM  2006       9          26         CA060724002      120060713G7810C5P156171       FLANGE                                  DHAV  DHC5  DHC5A       2803018NM                                                               EXHAUST SYS     FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) FLANGE HEIGHT IS 0.25 INCH INSTEAD OF 0.36 INCH.  THIS COULD LEAD TO JET PIPE FAILURE, WHICH IN TURN, COULD LEAD TO DAMAGE IN THE INTEGRITY OF THE WINGS AND SYSTEMS NEARBY.  CUSTOMERS ARE BEING NOTIFIED OF THIS NON-CONFORMANCE.  NOTE(08AUG06): ONLY MILITARY CUSTOMERS WERE AFFECTED. CAUSE: FLANGE HEIGHT DIMENSION WAS OVERLOOKED BY OPERATOR AND INSPECTOR. SPECIFIED FLANGE HEIGHT REQUIREMENT WILL BE FORMALLY STRESSED TO APPLICABLE OPERATORS AND INSPECTORS (DUE DATE: AUG/06). (TC NR 20060724002)                                                                                                                                                                                                                          2H72 4T    RT                             
20060814000632006081400063NE  2006       8          14         CA060724003      220060715G7240311583501       BURNER CAN                              PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  ENGINE          FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       4515 4                             PR0176                      (CAN) BRIGHT FLASHES COMING FROM EXHAUST STACKS, NO CHANGE TO INDICATIONS. 15 FLASHES IN 2 HOUR PERIOD.  ENGINE OUTER BURNER CAN FOUND INOPERATIVE, CERAMIC COATING FLAKING OFF AND IGNITING. REPLACED WITH OVERHAULED UNIT. GROUND RUN AND RELEASED SERVICEABLE. P/N - ON/OFF 3115835-01 S/N OFF A0006973, S/N ON 2K962. (TC NR 20060724003)                                                                                                                                                                                                                                                                                                                                                                                                   1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20060814000642006081400064EU  2006       8          14         CA060724004      120060717G771232448821        LIMITER                                 PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  ENGINE          FAILED          W      O   OTHER                                                                                           RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  NRNOT REPORTED   1                      CA       4516 11                            PR0175                      (CAN) PILOT SNAG: ENGINE POWER LOST IN FLIGHT HAD TO USE MANUAL OVERRIDE.  RECTIFICATION: REPLACED TORQUE LIMITER P/N 3244882-1, S/N C50254 WITH REMOVED SERVICEABLE UNIT FROM ENGINE S/N PR0116 P/N 3244882-1 S/N C50621. ALL APPLICABLE ENGINE RUNS COMPLETED AND CHECKS SERVICEABLE. (TC NR 20060724004)                                                                                                                                                                                                                                                                                                                                                                                                                                     1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20070516001622007051600162    2007       5          16         CA060724006      420060720G611305503214        BULKHEAD                                CESSNA172   172P        2072436CE  LYC   O320  O320D2J     41508EA  MCAULY1C160 1C160DTM    GL  PROP SPINNER    CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       250                                                            (CAN) THIS BULKHEAD HAS CRACKS DIRECTLY ABOVE THE BOLT HOLES APPROXIMATELY ONE INCH LONG RADIALY ALONG THE INNER BEND RADIUS ABOVE THE BOLT HOLE BUT NOT INTERSECTING THE BOLT HOLE. (TC NR 20060724006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1H71 3O3  ONT3A12    E274    5  NP910     
20070516001632007051600163    2007       5          16         CA060724007      420060721G611305503214        BULKHEAD                                CESSNA172   172P        2072436CE  LYC   O320  O320D2J     41508EA  MCAULY1C160 1C160DTM    GL  SPINNER         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       750                                                            (CAN) THIS BULKHEAD HAS CRACKS DIRECTLY ABOVE THE BOLT HOLES APPROXIMATELY ONE INCH LONG RADIALY ALONG THE INNER BEND RADIUS ABOVE THE BOLT HOLE BUT NOT INTERSECTING THE BOLT HOLE. (TC NR 20060724007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1H71 3O3  ONT3A12    E274    5  NP910     
20060926001632006092600163    2006       9          26         CA060725001      420060722G34449650976003206   SWITCH          HONEYWELL               AIRBUSA340  A340313            EU  GE    CFM56 CFM565A     13802NE                              GPWS            BURNED          W      A   UNSCHED LANDING                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA                                                                      (CAN) WHILE ENROUTE, ON A POLAR ROUTE IN THE MIDDLE OF HUDSON BAY, THE FLIGHT CREW REPORTED ACRID SMOKE COMING OUT OF OVERHEAD PANEL IN THE AREA OF THE TERRAIN SWITCH AND THE FAILURE OF THE GPWS.  THE SMOKE THEN DISSIPATED.  THE CREW DECLARED A PAN PAN (URGENCY), AND RETURNED TO YYZ, WHERE THE FLIGHT LANDED 30,000 KG OVERWEIGHT. (TC NR 20060725001)                                                                                                                                                                                                                                                                                                                                                                                  2L74 4F4  FRTA197    E29NE                
20060814000652006081400065NE  2006       8          14         CA060725002      220060721G73217436024         FUEL CONTROL                            BOEING737   737242C     1384478NM  PWA   JT8   JT8D9A      52048NE                              ENGINE          MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 EJ VIBRATION/BUFFET          WARNING INDICATION                                  CRCRUISE         1                      CA                                          708828                      (CAN) ENROUTE THE CREW ELECTED TO RETURN TO POINT OF DEPARTURE DUE TO A SUSPECTED ENGINE VIBRATION. AFTER ARRIVING, THE MAINTENANCE PERSONNEL INITIALLY REPLACED THE FORWARD ENGINE MOUNT ISOLATORS WITH NO APPARENT REMEDY OF THE PROBLEM. THE FCU WAS REPLACED AND THE ENGINE RUN UP WITH NO FURTHER VIBRATION INDICATION.THE AIRCRAFT WAS RETURNED TO SERVICE WITH NO FURTHER PROBLEMS. (TC NR 20060725002)                                                                                                                                                                                                                                                                                                                                  2L72 4F4  F  A16WE   E2EA                 
20060926001652006092600165CE  2006       9          26         CA060725004      120060720G261224412886        FIRE LOOP                               BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE  HARTZLHCE4A HCE4A3I     NE  FIRE DETECTION  UNKNOWN         W      E   ENGINE SHUTDOWN                                                                                 N  FALSE WARNING                                                                 CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE FLIGHT THE CREW RECEIVED A RT ENGINE FIRE ANNUCIATION. ALTHOUGH IT WAS DETERMINED THAT NO FIRE WAS PRESENT, PROCEDURES WERE FOLLOWED TO SHUTDOWN AND SECURE THE ENGINE IN FLIGHT AND THE DISCHARGE OF THE FIRE EXTINGUISHING AGENT.  MAINTENANCE FOUND THAT EITHER THE FORWARD OR AFT FIRE WIRE LOOP CAUSED THE ANNUNCIATION ALTHOUGH IT COULD NOT BE DETERMINED AS TO WHICH ONE AS THE FAULT MODE WAS NOT HARD AND THE SYSTEM RETURNED TO NORMAL OPS. BOTH LOOPS WERE REPLACED AS A PRECAUTION WITH NO REPEAT OF THE OCCURRENCE. IT IS ALSO POSSIBLE THAT THE FORWARD LOOP MAY HAVE BEEN TOO CLOSE TO THE STACK AND CAUSED THE FALSE WARNING AS WELL. (TC NR 20060725004)                                                  2L72 4T4  TRTA24CE   E26NE   5  CP10NE    
20070516001642007051600164NE  2007       5          16         CA060725005      220060723G7200                ENGINE                                  SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1        NE                                              MAKING METAL    W      O   OTHER                                                                                           J  WARNING INDICATION                                                            DEDESCENT        1                      CA       4111 1120                          9359                        (CAN) ON APPROACH, THE ENGINE CHIP LIGHT ILLUMINATED. THE PILOT LANDED THE HELICOPTER NORMALLY. THE ENGINE CHIP PLUGS WERE ALL REMOVED AND DEBRIS (METAL) WAS FOUND ON ALL PLUGS. METAL WAS ALSO FOUND ENTRAPPED IN THE OIL FILTER. THIS ENGINE WAS LAST SHOPPED IN MAY 2005 FOR MO2, MO4, MO5 AND FREEWHEEL OVERHAUL. THE TSO OF THE OVERHAULED COMPONENTS IS 295.9 HOURS (TC NR 20060725005)                                                                                                                                                                                                                                                                                                                                                  1G71 3U3  U  H9EU    E19EU                
20060814000982006081400098GL  2006       8          14         CA060725006      220060724G732323076061        GOVERNOR                                BELL  206   206B        1181511SW  ALLSN 250C  250C20      03013GL                                              INOPERATIVE     W      O   OTHER                                                                                           RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA            372                                                       (CAN)  UNIT HAD ABOUT 25.0 HOURS THIS INSTALL. PILOT REPORTED THAT GOVERNOR WOULD BLEED OFF IN FLIGHT BY 4 TO 5 PERCENT THEN COME BACK TO NORMAL AFTER A FEW SECOND 10 TO 15 SECONDS. THEN IT WOULD BE FINE FOR SOME TIME. UPON REPORTING THIS THE AIRCRAFT WAS REMOVED FROM SERVICE AND A NEW GOVERNOR WAS INSTALLED. (TC NR 20060725006)                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3U3  U  H2SW    E4CE                 
20060926001692006092600169WP  2006       9          26         CA060725007      120060725G7820C16932          MUFFLER                                 ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              EXHAUST         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       398                                                            (CAN) DURING A ROUTINE 100 HR INSPECTION, IT WAS NOTED THAT THE MUFFLER/TAILPIPE ASSY WAS DISTORTED AND CRACKED AT THE OUTLET PIPE. THE CRACK WAS NOTICED AFTER THE CABIN HEATER JACKET WAS REMOVED. THE CRACK WOULD NOT BE NOTICEABLE WITH THE CABIN HEATER JACKET INSTALLED. THE CABIN CARBON MONOXIDE DETECTOR SYSTEM SHOWED NO INDICATIONS OF EXCESSIVE CARBON MONOXIDE. IT IS NOTED THAT IF THE AIRCRAFT WAS FLYING IN COLD CONDITIONS, WHERE THE CABIN HEAT WOULD BE SELECTED (TC NR 20060725007)                                                                                                                                                                                                                                         1G71 3O3  O  H11NM   1E4                  
20060926001712006092600171WP  2006       9          26         CA060725009      120060720G2120D0571           AIR BOX                                 ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              OUTER HOUSING   CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       398                                                            (CAN) DURING A ROUTINE 100 HR INSPECTION, A CRACK WAS NOTICED IN THE ABOVE PART. THERE IS A CHANCE THAT THE CRACK COULD BE THE RESULT OF CLEARANCE ISSUES WHEN REMOVING AND INSTALLING THE AIRBOX FROM THE AIRFRAME. THE PART WAS REPLACED WITH A NEW PART, AND IT WAS NOTED THAT THE NEW PART IS NOW MADE FROM FIBERGLASS, WHERE THE ORIGINAL PART IS MADE FROM A PLASTIC MATERIAL. THIS COULD ALSO BE ANOTHER REASON FOR THE CRACK, OR AN ATTRIBUTE. THE PART HAS 398.6 HRS SINCE NEW. THE AIRCRAFT WAS MANUFACTURED NEW IN OCTOBER 2005. (TC NR 20060725009)                                                                                                                                                                                 1G71 3O3  O  H11NM   1E4                  
20060926001722006092600172EA  2006       9          26         CA060725010      220060723G8530416453          PUSHROD                                 GRUMANTS2   TS2ACALFORST3951102WP  WRIGHTR1820 982C9HE2    67020EA  HAMSTD43D   43D51       NE  ENGINE          BROKEN          W      E   ENGINE SHUTDOWN                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA            500                                                       (CAN) PUSHROD BROKE AT TOP BALLEND AT ROCKER ARM ON NR 1 CYLINDER EXHAUST VALVE. PUSH ROD REPLACED AND ENGINE GROUND RUN, CHECKED OK. AIRCRAFT TEST FLOWN AND FOUND SATISFACTORY (TC NR 20060725010).                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2H72 4R4  R  A25WE   E259    6  CP8879    
20060814001242006081400124NE  2006       8          14         CA060726001      220060720G7421955075400       IGNITER                                 SNIAS 350   AS350BA     8680817EU  TMECA ARRIELARRIEL1B    6OO30NE                              ENGINE          LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       515                                4396                        (CAN) INSULATION WITHIN IGNITOR FOUND LOSE.  IN LIGHT OF PAST INCIDENCE OF ENGINE FOD, IGNITORS WERE CHANGED.  IGNITOR P/N 955075400/CH34745 (TC NR 20060726001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1G71 3U3  UNCH9EU    E19EU                
20060814001092006081400109NE  2006       8          14         CA060726002      220060711G72502292253850      TURBINE BLADES                          SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1        NE                              1ST STAGE       FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       254  254                                                       (CAN) THE PILOT SHUTDOWN THE AIRCRAFT TO HOOK UP HIS WATER BUCKET, AFTER A SHORT TIME PERIOD OF APPROXIMATE 8 TO 10 MINUTES HE ATTEMPTED TO RESTART THE AIRCRAFT. THE STARTER WOULD NOT TURN THE ENGINE, A BORESCOPE WAS USED TO LOOK INSIDE THE ENGINE AND FOUND THAT THE 1ST STAGE TURBINE BLADE HAD RUBBED. THE M03 WAS THEN REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20060726002)                                                                                                                                                                                                                                                                                                                                              1G71 3U3  U  H9EU    E19EU                
20060926001742006092600174EU  2006       9          26         CA060726003      120060725G631035013001        FREEWHEEL UNIT                          SNIAS 350   AS350*             EU  ALLSN 250C  250C30      03013GL                              MAIN ROTOR      MAKING METAL    W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       5074 61                                                        (CAN) AFTER INSTALLING A OVERHAULED FREEWHEEL, METAL WAS FOUND FOUR SEPARATE TIME IN 61.1 HOURS, SILVER FLAKES FOUND ON CHIP PLUG. (TC NR 20060726003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1G71 3U3  U  H9EU    E1GL                 
20060926001772006092600177NM  2006       9          26         CA060726004      120060726G271082742409001     CONTROL UNIT                            BOMBDRDHC8  DHC8402     1390042NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  AILERONS        WORN            W      O   OTHER                                                                                           W  INADEQUATE Q C                                                                NRNOT REPORTED   1                      CA       1350                                                           (CAN) RT AILERON CABLES PN: 82742409-001 ( WS Y14.25-Y232.00) AND CABLE PN: 82742410-001 (WS Y14.25-Y258.00) WERE APPROACHING PERMISSIBLE WEAR LIMITS AT PULLEY CONTACT AREAS.  CABLES REPLACED  THIS PROBLEM IS ALREADY KNOWN BY MFG REF TO ALL OPERATOR MESSAGE NR AOM 122 AND SB 84-27-26.   INSPECTED THE A/C IN APRIL 2004 FOLLOWING RECEPTION OF AOM122 AND AILERON CABLES REPLACED DUE FOUND WORN.  WE ALSO REINSPECTED THE A/C IN MAY 2005 FOLLOWING RECEPTION OF THE S/B 84-27-26 AND AILERON CONTROL CABLES REPLACED AGAIN DUE STILL FOUND WORN.  IN JULY 2006 DURING A FLAP INSPECTION OUR AME (KNOWING THE AILERON CONTROL CABLE PROBLEMS) WIPE THE AILERON CABLES WITH A RAG TO FOUND THAT SOME WIRES WERE BROKEN.  THESE CABLES MU2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
20060808000912006080800091EA  2006       8          8          CA060726005      220060724G7261ES48110         OIL FILTER                              PIPER PA31  PA31        7103102SO  LYC   O540  TIO540A2B   41532EA  HARTZLHCE2Y HCE2YR2     GL  ENGINE          LEAKING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                          RL103161                    (CAN) DURING POST RUN UP INSPECTION OF REGULAR INSPECTION APPROXIMATE ONE FLUID OZ OF OIL WAS NOTED LEAKING FROM THE NEWLY INSTALLED OIL FILTER. IT IS SUSPECTED THAT A SIMILAR DEFECT BUT OF LESSER DEGREE MAY NOT BE PICKUP BY POST RUN UP INSPECTION AND MAY CAUSE A FINE OIL MIST ON HOT TURBO CHARGER AND EXHAUST PARTS ON THIS AND SIMILAR ENGINE INSTALLATIONS. (TC NR  20060726005)                                                                                                                                                                                                                                                                                                                                                     1L72 3O3  O  A20SO   E14EA   5  CP9EA     
20060808000922006080800092CE  2006       8          8          CA060726006      120060726G8011EBB124A         DRIVE ASSY      PRESTOLITE              CESSNA150   152         2071835CE  LYC   O235  O235L2C     41505EA  SNSNCH72C   72CK        EA  STARTER         BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            1102  E042509                                             (CAN) PILOT TRIED TO START ENGINE BUT THE STARTER WOULD NOT ENGAGE. AIRCRAFT BROUGHT INTO HANGER AND STARTER WAS REMOVED FROM ENGINE. IT WAS DISCOVERED THAT THE TEETH ON THE BENDIX DRIVE THAT ENGAGE THE RING GEAR HAD SHEARED OFF. (TC NR 20060726006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3O3  ONT3A19    E223    5  NP9045    
20060926001792006092600179CE  2006       9          26         CA060726007      120060724G2435230760011       BRUSHES         LEARSIEGLER             CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              STARTER GEN     WORN            W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA            3     2004                                                (CAN) DURING BASE INSPECTION, LT ENGINE COWL WAS COVERED WITH BLACK DUST. UPON FURTHER INSPECTION THE STARTER/GEN WAS REMOVED AND THE BRUSHES INSPECTED TO BE WORN OVER HALF LIFE. STARTER/GEN HAD ONLY 2.7 HRS SINCE OVERHAUL. STARTER/GEN SENT FOR WARRANTY AND TEARDOWN REPORT. (TC NR 20060726007)                                                                                                                                                                                                                                                                                                                                                                                                                                          1L72 4F4  F  A22CE   E1NE                 
20060926001812006092600181SW  2006       9          26         CA060727001      120060727G6220204011116001    NUT             BELL                    BELL  205   205A1       1181414SW  LYC   T53   T5317A      41549NE                              M/R HUB         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                  ADA50015                                            (CAN) THIS IS AN ON CONDITION ITEM. SO HISTORY MAY NOT BE ACCURATE. M/R HUB ASSY HAS 18437.6 TIME SINCE NEW.  M/R HEAD ASSY WAS IN FOR O/H AND REQUIRES  ACORN NUTS TO BE NDT. THIS ONE WAS FOUND CRACKED. (TC  NR 20060727001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1G71 4U4  U  H1SW    E17EA                
20060926001832006092600183SW  2006       9          26         CA060728001      120060711G2910206076437003    CHECK VALVE                             BELL  412   412EP       1182205SW  PWA   PT6T  PT6T3       52045EA                              HYD SYS 2       JAMMED          W      O   OTHER                                                                                           MJ OVER TEMP                 WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA                                                                      (CAN) UPON FIRST GROUND RUN OF M412 DURING MANUFACTURING FTP`S (WITHOUT M/R BLADES INSTALLED), A NOISE (BANG) WAS HEARD TWICE AND HYDR PRESSURE RAISED TO +1300 PSI ON THE GAGE. PILOT SHUTDOWN THE HYDR SYSTEM AND ABORTED GROUND RUN FOR INVESTIGATION.  FURTHER INVESTIGATION REVEALED THAT A SWIRL OF COPPER METAL (CHIPS) JAMMED THE HYDRAULIC CHECK VALVE IN AN OPEN POSITION WHICH ALLOWED REVERSED FLOW AND AN HYDR LOCK BY PRESSURIZING THE PUMP CASE DRAIN, FOLLOWED BY A TEMPERATURE RISE. HYDRAULIC COMPONENTS REPLACED AND AIRCRAFT RETURNED TO SERVICE. FURTHER LAB TESTING WERE ABLE TO REPRODUCE THE PROBLEM AND TEMPERATURE WAS TWICE THE NORMAL RANGE WITHIN 4 MIN. OF OPERATION. THE SOURCE OF THE DEBRIS WAS NOT FOUND COULD1G72 4U4  U  H4SW    E22EA                
20060926001862006092600186NM  2006       9          26         CA060728002      120060725G5270                SWITCH                                  BOEING727   727225      1384077NM  PWA   JT8   JT8D15A     52051NE                              CARGO DOOR      OUT OF RIG      W      JA  DUMP FUEL               UNSCHED LANDING                                                         N  FALSE WARNING                                                                 CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB THROUGH FL210 AND 6.0 PSID CABIN DIFFERENTIAL THE CARGO DOOR UNSAFE LIGHT INDICATION ILLUMINATED. AIRCRAFT DUMPED FUEL AND RETURNED TO STATION, DURING APPROACH THE CARGO DOOR UNSAFE LIGHT EXTINGUISHED. UPON INSPECTION MAINTENANCE FOUND DOOR CLOSE MICRO SWITCH OUT OF RIG. SWITCH ADJUSTED IAW AEI MM CHAPTER 24 PAGE 26. CONTRIBUTING FACTORS: PRIOR TO DEPARTURE THE AIRCRAFT WAS UNDERGOING THE INCORPERATION OF SB AEI 04-02 REV 1R. CLARIFICATION OF RIGGING PROCEDURES WAS REQUESTED FROM AEI. (TC NR 20060728002)                                                                                                                                                                                                2L73 4F4  F  A3WE    E2EA                 
20060926001872006092600187SW  2006       9          26         CA060728003      120060714G65102040406009      BEARING         BELL                    BELL  205   205A1       1181414SW  LYC   T53   T5313B      41549NE                              TAIL ROTOR DRIVEFAILED          W      C   ABORTED TAKEOFF                                                                                 DF INFLIGHT SEPARATION       FLT CONT AFFECTED                                   TOTAKEOFF        1                      CA                  A2079238                                            (CAN) THE TAIL ROTOR DRIVESHAFT HANGER HAD BEEN INSTALLED THE NIGHT BEFORE THE FAILURE. WE SUSPECT AN INNER COUPLING FAILURE. THE SUSPECT COUPLING HAD BEEN RECOATED JUST BEFORE INSTALLATION BY USING AN AMS2451/4 PROCESS. (TC NR 20060728003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1G71 4U4  U  H1SW    E17EA                
20060808000952006080800095NE  2006       8          8          CA060728004      220060727G7230                FAN BLADE                               CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              ENGINE          DISAPPEARED     W      EFA ENGINE SHUTDOWN         ACTIVATE FIRE EXT.      UNSCHED LANDING                                 ERJVIBRATION/BUFFET          PARTIAL RPM/PWR LOSS      WARNING INDICATION        CLCLIMB          1                      CA       10896                              873549                      (CAN) DURING CLIMB OUT AT 18,000FT, THE COCKPIT CREW HEARD A LOUD BANG, FOLLOWED BY HIGH VIBES ON THE NR 1 ENGINE. FIRE WARNING CAME UP, PILOT DISCHARGED THE FIRE BOTTLES AND SHUTDOWN THE ENGINE. EMERGENCY WAS DECLARED AND AIRCRAFT RETURNED TO BARCELONA, WHERE IT PERFORMED AN UNEVENTFULL SINGLE-ENGINE LANDING. INITIAL REPORT SAYS ONE FAN BLADES DISAPPEARED, JET PIPE IS BURNED AND CRACKED.  FURTHER INFORMATION WILL BE PROVIDED ONCE THE ENGINE STRIP REPORT IS AVAIALBLE. (TC NR 20060728004)                                                                                                                                                                                                                                    2L72 4F4  FRTA21EA   E15NE                
20060926001882006092600188    2006       9          26         CA060728005      420060721G23128992125014      CONTROL PANEL                           AIRBUS310   A310300     3930305EU  GE    CF6   CF680C2*         GL                              VHF             SMOKE           W      H   DEACTIVATE SYST/CIRCUITS                                                                        B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA       2410124101 4520                                                (CAN) DURING FLIGHT, LIGHT SMOKE CAME FROM THE NR 1 VHF CONTROL PANEL. THE CIRCUIT BREAKER WAS PULLED AND THE FLIGHT PROCEEDED WITHOUT ANY FURTHER PROBLEM. THE PANEL WAS REPLACED AT THE ARRIVAL STATION AND WAS SYSTEM CHECKED SERVICEABLE. PANEL WAS ROUTED TO THE VENDOR FOR INVESTIGATION.  (TC NR 20060728005)                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F4  FRTA35EU   E23EA                
20060808000962006080800096NE  2006       8          8          CA060728006      220060722G7261                ENGINE                                  CNDAIRCL601 CL6012A12   1900303EA  GE    CF34  CF343B1          NE                              RIGHT           OIL CONSUMPTION W      E   ENGINE SHUTDOWN                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) AIRCRAFT HAD TO SHUTDOWN THE RT ENGINE DURING FLIGHT, DUE TO LOW OIL PRESSURE. APPROX 3 HOURS INTO THE FLIGHT, THE PILOT REPORTED THE OIL PRESSURE WAS FLUCUTATING BETWEEN 45 AND 65 PSI, THEN DROPPED AGAIN TO 35 AND 55 PSI, AND FINALLY GOT A STEADY LOW OIL PRESSURE LIGHT. THIS IS WHEN THE PILOT SHUTDOWN THE RT ENGINE, AND DIVERTED.  AN INSPECTION REVEALED THE RT ENGINE WAS 4 QTS LOW ON OIL. THE PILOTS HAD ALREADY SERVICED THIS ENGINE WITH 2 QTS, PRIOR TO  LEAVING.  APPEARS THE AIRCRAFT USED 4 QTS OF OIL IN THAT 3 HOUR PERIOD. AN OIL CONSUMPTION CHECK WAS PERFORMED,  AND WAS FOUND TO BE WITHIN LIMITS. THE AIRCRAFT IS UNDERGOING FURTHER TROUBLESHOOTING. (TC NR 20060728006)                                    2L72 4F4  FRTA21AE   E15NE                
20060808000972006080800097WP  2006       8          8          CA060728007      220060727G7200                ENGINE                                  DHAV  DHC3  DHC3        2800202EA  GARRTTTPE331TPE33110R   0517 WP  HARTZLHCB4T HCB4TN5     GL                  VIBRATES        W      E   ENGINE SHUTDOWN                                                                                 E  VIBRATION/BUFFET                                                              DEDESCENT        1                      CA                                                                      (CAN) DURING DESCENT FOR FLOAT LANDING ON WATER,  PILOT NOTICED VIBRATION IN ENGINE . ENGINE SHUTDOWN, PROP FEATHERED. AIRCRAFT LANDED WITHOUT INCIDENT. ENGINE REMOVED SENT TO REPAIR FACILITY. (TC NR 20060728007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H71 3R4  T  A815    E4WE    6  CP40EA    
20060808000982006080800098EA  2006       8          8          CA060729001      120060724G5610NP1393226       WINDOW                                  CNDAIRCL600 CL6002C10   1390015EA  GE    CF34  CF348C1          NE                              COCKPIT         CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         APAPPROACH       1                      CA       8565                                                           (CAN) DESENDING THROUGH 13000 FT - F/O SIDE WINDOW CRACKED. TAXING TO GATE WINDOW (F/O SIDE WINDOW) CRACKED MORE. WINDOW WAS REPLACED IAW AMM. SIDE WINDOW IS PRE SB NP139322-001 (TC NR 20060729001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F4  FRTA21EA   EOOO63EN             
20060808000992006080800099CE  2006       8          8          CA060731001      120060727G2720656530129       GUARD                                   CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              RUDDER CONTROL  DELAMINATED     W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       7217                                                           (CAN) WHEN MOVING THE RUDDER WITH HAND PRESSURE OF APPROXIMATELY 10 DEGREES EITHER SIDE OF CENTER A NOISE ALONG WITH A ROUGH SNAGGING FEEL NOTICED.  TRACING THE NOISE DOWN THROUGH THE TAIL INTO THE CABIN BETWEEN FLIGHT STATION 166 TO 180.  THE CABLE GUARD PN 6565301-29 FOUND TO BE DISPLACED FORWARD OUT OF REAR CLAMP AND CABLE END CONTACTING THE END OF THE CABLE GUARD.  THE CABLE GUARD WAS REMOVED AND INSPECTED, FOUND INNER LAMINATE OF THE PHENOLIC DELAMINATED WITH WHAT LOOKED LIKE A CONTACT POINT FROM CONTACT WITH THE CABLE END OR TURN BARREL NEAR THE FWD END AND THE GUARD WAS DAMAGED ON THE AFT END FROM CONTACT WITH THE CABLE END. (TC NR 20060731001)                                                             1L72 4F4  F  A22CE   E1NE                 
20060926001912006092600191EA  2006       9          26         CA060731002      220060713G7210310152501       PLANETARY GEAR                          BEECH 99    99          1154002CE  PWA   PT6   PT6A28           EA  HARTZLHCB3T HCB3TN3     GL  ENGINE          MAKING METAL    W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA            184                           PCE41483                    (CAN) METAL CONTAMINATION WAS FOUND ON THE CHIP DETECTOR.  METAL ORIGINATED FROM RGB AND WAS THE RESULT OF SIGNIFICANT MATERIAL LOSS BETWEEN THE 1ST STAGE SUN GEAR AND THE 1ST STAGE PLANETARY GEARS. THIS IS OUR 2ND SUCH CASE WITH TIME CONTINUED GEARS. (TC NR 20060731002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L72 3T4  T  A14CE   E4EA    6  CP15EA    
20060808001002006080800100EA  2006       8          8          CA060731003      220060728G852013828           CRANKCASE                               PIPER PA31  PA31350     7103110SO  LYC   O540  TIO540J2BD  41532EA  HARTZLHCE3Y HCE3YR2A    GL  ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            517                           L57468A                     (CAN) DURING A ROUTINE INSPECTION AN AME VISUALLY DISCOVERED A CRACK 2-3 INCHES IN LENGTH. THE CRACK IS LOCATED BETWEEN CYLINDERS 3 AND 5 IN THE VICINITY OF THE LOWER RIB. PREVIOUSLY NO DISCREPANCIES HAD BEEN NOTED. THE ENGINE WAS SUBSEQUENTLY REMOVED FOR REPAIR AT AN APPROVED ENGINE OVERHAUL SHOP. THE TTSN FOR THIS CASE COULD NOT BE OBTAINED. THIS CASE WAS INSTALLED 516.8 HRS EARLIER BECAUSE OF ANOTHER INCIDENT OF CRACKED CASE.                                                                                                                                                                                                                                                                                                1L72 3O3  O  A20SO   E14EA   5  CP33EA    
20060926001952006092600195CE  2006       9          26         CA060731005      120060728G7714991214736       INDICATOR                               CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              N2 SPEED        SHORTED         W      K   NONE                                                                                            N  FALSE WARNING                                                                 ININSP/MAINT     1                      CA                                                                      (CAN) DURING TROUBLESHOOTING OF A POSSIBLE N2 OVERSPEED OF BOTH ENGINES, THE N2 GAGE WAS TESTED BY SIMULATING SPEEDS WITH VOLTAGE AT SEVERAL FREQUENCIES. WHEN VALUES WERE BROUGHT AT LEVELS TO ILLUMINATE THE RED OVERSPEED WARNING LIGHT, IT WAS NOTED THAT THE INDICATION WAS CROSSED MEANING THAT FOR A READING OF 96 PERCNET N2 AND ABOVE ON LT ENGINE THE RT WARNING LIGHT IN THE GAGE ILLUMINATES.  THE REVERSE CONDITION HAPPENS WHEN THE RT ENGINE INDICATION IS TESTED (N2 READING), MEANING THAT THE LT INDICATION (RED WARNING LIGHT) ILLUMINATES. THE SUSPECT GAUGE WAS REPLACED AND THE SYSTEM GROUND CHECKED SERVICEABLE. (TC NR 20060731005)                                                                                    1L72 4F4  F  A22CE   E1NE                 
20060814001102006081400110NE  2006       8          14         CA060731006      220060628G73203031829         LINE                                    AIRTRCAT802 AT802       0390305SW  PWA   PT6   PT6A67A     52043NE  HARTZLHCB5M HCB5MA3     GL  P3 AIR TUBE     FRACTURED       W      A   UNSCHED LANDING                                                                                 XJ ENGINE FLAMEOUT           WARNING INDICATION                                  APAPPROACH       1                      CA                                                                      (CAN) THE ENGINE WAS REPORTED TO FLAME OUT DURING APPROACH RESULTING IN THE AIRCRAFT LANDING SHORT OF THE RUNWAY.  SUBSEQUENT INSPECTION REVEALED A FRACTURED P3 PNEUMATIC LINE TO THE FUEL CONTROL.  MFG WILL MONITOR INVESTIGATION AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060731006)                                                                                                                                                                                                                                                                                                                                                                                                                                             1L71 3T4  TNCA19SW   E26NE   6  CP44GL    
20060814001122006081400112EA  2006       8          14         CA060731007      220060629G7261                OIL SYSTEM                              DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A27      52043EA                              ENGINE          LEAKING         W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         KRJFLUID LOSS                PARTIAL RPM/PWR LOSS      WARNING INDICATION        CLCLIMB          1                      CA                                          41601                       (CAN) DURING CLIMB, ENGINE OIL PRESSURE WAS REPORTED TO FLUCTUATE FOLLOWED BY A LOSS IN OIL PRESSURE. THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT RETURNED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED INTERNAL OIL LEAKAGE.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060731007)                                                                                                                                                                                                                                                                                                                                                                                                   1H72 3T4  TRTA9EA    E4EA                 
20060814001132006081400113NE  2006       8          14         CA060731008      220060705G7321                FUEL CONTROL                            CESSNA500   550         2076604CE  PWA   530   PW530A           NE                              ENGINE          UNSERVICEABLE   W      O   OTHER                                                                                           XJ ENGINE FLAMEOUT           WARNING INDICATION                                  APAPPROACH       1                      CA                                                                      (CAN) THE ENGINE WAS REPORTED TO FLAME OUT ON APPROACH.  THE FUEL CONTROL UNIT WAS SUBSEQUENTLY REPLACED.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060731008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L72 4F4  F  A22CE   E00053EN             
20060814001142006081400114NE  2006       8          14         CA060731009      220060704G7250                TURBINE BLADES                          AYRES S2T   STRT34      0970106SO  PWA   PT6   PT6A34AG    52053NE                              ENGINE          FRACTURED       W      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA                                          PH0243                      (CAN) THE ENGINE WAS REPORTED TO LOSE ALL POWER IN CRUISE. A DEAD-STICK LANDING WAS PERFORMED IN A  FIELD RESULTING IN AIRFRAME DAMAGE.  SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES.  MFG WILL INVESTIGATE AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20060731009)                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L71 3T4  T  A3SW    E4EA                 
20060814000662006081400066EA  2006       8          14         CA060731010      220060705G7200                ENGINE                                  BELL  412   412         1182202SW  PWA   PT6T  PT6T3       52045EA                                              MAKING METAL    W      O   OTHER                                                                                           XJ ENGINE FLAMEOUT           WARNING INDICATION                                  HOHOVERING       1                      CA                                                                      (CAN) THE ENGINE WAS REPORTED TO LOSE POWER IN HOVER ACCOMPANIED BY A CHIP DETECTOR INDICATION.  SUBSEQUENT INSPECTION REVEALLED LOSS OF DRIVE TO THE ACCESSORY GEARBOX.  MFG WILL MONITOR INVESTIGATION AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20060731010)                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1G72 4U4  U  H4SW    E22EA                
20060814000672006081400067EA  2006       8          14         CA060731011      220060704G7200                ENGINE                                  DHAV  DHC7  DHC7103     2802710EA  PWA   PT6   PT6A50      52043EA  HAMSTD24PF  24PF305     GL                  MALFUNCTIONED   W      C   ABORTED TAKEOFF                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      TOTAKEOFF        1                      CA                                          86312                       (CAN) ON TAKEOFF ROLL THE ENGINE EMITTED A LOUD NOISE AND SMOKE WAS SEEN EMERGING FROM THE EXHAUST.  TAKEOFF WAS ABORTED AND THE ENGINE SECURED. MFG WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20060731011)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2H74 4T4  T  A20EA   E4EA    6  CP1NE     
20060809001962006080900196NE  2006       8          9          CA060731012      220060710G7230                DIFFUSER                                AEROSPATR72 ATR72212A   8680902EU  PWA   PW120 PW127            NE                              LOW COMPRESSOR  FRACTURED       W      C   ABORTED TAKEOFF                                                                                 J  WARNING INDICATION                                                            TOTAKEOFF        1                      CA                                                                      (CAN) DURING TAKEOFF ROLL, ENGINE TEMPERATURE WAS SEEN EXCEEDING LIMITS AND THE TAKE-OFF WAS ABORTED.  SUBSEQUENT INSPECTION REVEALED A FRACTURED LOW PRESSURE DIFFUSER TUBE.  THE TUBE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20060731012)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2H72 4T4  TRTA53EU   E20NE                
20060809001972006080900197EA  2006       8          9          CA060731013      220060712G7230                COMPRESSOR                              BEECH 1900  1900C       1154161CE  PWA   PT6   PT6A65B     52043EA                              ENGINE          SEIZED          W      E   ENGINE SHUTDOWN                                                                                 BXJSMOKE/FUMES/ODORS/SPARKS  ENGINE FLAMEOUT           WARNING INDICATION        CRCRUISE         1                      CA                                                                      (CAN) DURING FLIGHT AN OIL SMELL WAS REPORTED IN THE COCKPIT.  THE ENGINE SUBSEQUENTLY SURGED ACCOMPANIED BY A LOW OIL PRESSURE WARNING AND WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED OIL LEAKAGE AND A PARTIALLY SEIZED HIGH PRESSURE COMPRESSOR.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060731013)                                                                                                                                                                                                                                                                                                                                                                                 2L72 4T4  TRTA24CE   E4EA                 
20060809001982006080900198EA  2006       8          9          CA060731014      220060714G7320312241908       METERING UNIT                           BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                              ENGINE          MALFUNCTIONED   W      E   ENGINE SHUTDOWN                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE, THE AIRCRAFT YAWED ACCOMPANIED BY A LOSS IN ENGINE TORQUE.  THE ENGINE WAS SHUTDOWN IN FLIGHT.  THE FUEL METERING UNIT WAS SUBSEQUENTLY DETERMINED TO BE UNSERVICEABLE AND WAS REPLACED. (TC NR 20060731014)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2H72 4T4  TRTA13NM   E00062EN             
20060809001992006080900199EU  2006       8          9          CA060731015      120060716G7712311629401A      LIMITER                                 PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  TORQUE          MALFUNCTIONED   W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             DEDESCENT        1                      CA                                                                      (CAN) IN DESCENT THE ENGINE WOULD NOT RESPOND TO THROTTLE INPUT. THE MANUAL FUEL CONTROL OVER-RIDE WAS ENGAGED, AN EMERGENCY DECLARED AND THE AIRCRAFT LANDED WITHOUT INCIDENT.  THE ENGINE TORQUE LIMITER WAS SUBSEQUENTLY DETERMINED TO BE FAULTY AND WAS REPLACED. (TC NR 20060731015)                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20060810000202006081000020NE  2006       8          10         CA060731016      220060525G7250                TURBINE BLADES                          CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE                              ENGINE          FRACTURED       W      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA                                          PC0951                      (CAN) DURING CRUISE THE ENGINE EMITTED A NOISE ACCOMPANIED BY AN UNCOMMANDED REDUCTION IN POWER.  THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED A FRACTURED POWER TURBINE BLADE.  MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060731016)                                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3T3  T  A37CE   E4EA                 
20060810000212006081000021NE  2006       8          10         CA060731017      220060719G7200                ENGINE                                  BELL  212   212         1181420SW  PWA   PT6T  PT6T3B      52045NE                                              MAKING METAL    W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                          63196                       (CAN) THE ENGINE EMITTED A NOISE IN FLIGHT ACCOMPANIED BY A RISE IN ITT TEMPERATURE. THE ENGINE WAS SHUTDOWN AND AN UNSCHEDULED LANDING CARRIED OUT.  SUBSEQUENT INSPECTION REVEALED METAL DEBRIS IN THE EXHAUST. MFG WILL MONITOR THE INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20060731017)                                                                                                                                                                                                                                                                                                                                                                                                            1G71 4U4  U  H4SW    E22EA                
20060810000222006081000022NE  2006       8          10         CA060731018      220060711G7200                ENGINE                                  AYRES S2    S2RT34NORMAL0970106SO  PWA   PT6   PT6A34AG    52053NE                                              VIBRATES        W      A   UNSCHED LANDING                                                                                 ER VIBRATION/BUFFET          PARTIAL RPM/PWR LOSS                                CRCRUISE         1                      CA                                          PH0054                      (CAN) DURING FLIGHT THE ENGINE WAS REPORTED TO LOSE POWER ACCOMPANIED BY HEAVY VIBRATIONS.  A FORCED LANDING WAS CARRIED OUT RESULTING IN AIRFRAME DAMAGE.  MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060731018)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L71 3T4  T  A3SW    E4EA                 
20060810000232006081000023NE  2006       8          10         CA060731019      220060722G7200                ENGINE                                  BELL  212   212         1181420SW  PWA   PT6T  PT6T3B      52045NE                                              FLAMED OUT      W      A   UNSCHED LANDING                                                                                 XJ ENGINE FLAMEOUT           WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) FOLLOWING TAKE-OFF THE ENGINE EMITTED A NOISE AND FLAMED OUT.  SUBSEQUENT GROUND INSPECTION REVEALED EXERNAL OIL LEAKAGE.  MFG WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060731019).                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1G71 4U4  U  H4SW    E22EA                
20060814000682006081400068NE  2006       8          14         CA060731020      220060722G7320                HMU                                     DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE                              ENGIEN          MALFUNCTIONED   W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      CA                                          120282                      (CAN) DURING TAKE-OFF ROLL THE ENGINE MASTER CAUTION WARNING ANNUNCIATED. IN CLIMB, ENGINE TORQUE REDUCED UNCOMMANDED AND THE ENGINE WAS SHUTDOWN IN FLIGHT.  THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  THE ELECTRONIC AND HYDROMECHANICAL FUEL CONTROLS WERE SUBSEQUENTLY REPLACED AND THE AIRCRAFT RETURNED TO SERVICE.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060731020)                                                                                                                                                                                                                                                                                                                    2H72 4T4  TRTA13NM   E20NE                
20060810000242006081000024NE  2006       8          10         CA060731021      220060727G7200                ROTOR                                   UROCOPEC135 EC135P1     8680990EU  PWA   PW206 PW206B      0    NE                              ENGINE          SEIZED          W      A   UNSCHED LANDING                                                                                 EJ VIBRATION/BUFFET          WARNING INDICATION                                  CLCLIMB          1                      CA                                          BB0122                      (CAN) DURING CLIMB THE ENGINE ELECTRONIC CONTROL REVERTED TO MANUAL AND THE PILOT ELECTED TO LAND.  ON DESCENT THE AIRCRAFT BEGAN TO VIBRATE AND THE PILOT AUTOROTATED.  SUBSEQUENT INSPECTION REVEALED DAMAGE TO ENGINE REAR MOUNT AND ROTOR SEIZURE. MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060731021)                                                                                                                                                                                                                                                                                                                                                                                            1G72 3U3  UO H88EU   E42NE                
20060810000252006081000025EA  2006       8          10         CA060731022      220060720G7250                TURBINE BLADES                          BEECH 1900  1900C       1154161CE  PWA   PT6   PT6A65B     52043EA                              ENGINE          FRACTURED       W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      CA                                          3200832167                  (CAN) FOLLOWING TAKEOFF THE ENGINE EMITTED A NOISE ACCOMPANIED BY AN UNCOMMANDED REDUCTION IN POWER. THE ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES.  MFG WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20060731022)                                                                                                                                                                                                                                                                                                                                                                        2L72 4T4  TRTA24CE   E4EA                 
20060810000262006081000026NE  2006       8          10         CA060801001      220060604G7250                TURBINE BLADES                          BOEING717   717200      1383700NM  RROYCEBR700 BR700715A130     NE                              ENGINE          DAMAGED         W      C   ABORTED TAKEOFF                                                                                 MT OVER TEMP                 ENGINE CASE PENETRATION                             TOTAKEOFF        1                      CA                                          13266                       (CAN) ON INITIAL TAKEOFF ROLL, ENGINE 13266ON A/C 477-1 SURGED AND EXPERIENCED A BRIEF OVER TEMPERATURE. MAX TGT WAS 903 DEG C FOR LESS THAN A FEW SECONDS. METAL IN TAIL PIPE WAS FOUND AS WELL AS A HOLE IN THE HP T CASE. ENGINE IS UNDER INVESTIGATION AT RRC. FURTHER DETAIL WILL BE SUBMITTED WHEN AVAILABLE. (TC NR 20060801001)                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FTRA6WE    E00061EN             
20060926001962006092600196EA  2006       9          26         CA060801003      120060713G3320BR90002         BALLAST                                 CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30015NE                              CABIN LIGHTS    ODOR            W      K   NONE                                                                                            B  SMOKE/FUMES/ODORS/SPARKS                                                      ININSP/MAINT     1                      CA                                                                      (CAN) DURING PASSENGER BOARDING AND UPON ENTRY TO FLIGHT DECK A STRONG ELECTRICAL SMELL WAS APPARENT AND PROGRESSIVELY GOT WORSE. PASSENGERS WERE DE-PLANED. LINE MAINTENANCE CREW FOUND FORWARD BOARDING LIGHT BALLAST P/N BR9000-2 BURNED. THE BURNED BALLAST WAS REPLACED, GROUND CHECKS PERFORMED AND AIRCRAFT RETURNED TO SERVICE. AIRFRAME HOURS WERE 25426:25 AND CYCLES WERE: 20767. (TC NR 20060801003)                                                                                                                                                                                                                                                                                                                                2L72 4F4  FRTA21EA   E15NE                
20061018000772006101800077SW  2006       10         18         CA060801004      120060722G5302206031329103S   FITTING                                 BELL  206   206B        1181511SW  ALLSN 250C  250C20      03013GL                              TAIL BOOM       CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       16806                                                          (CAN) A CRACK WAS FOUND FROM THE AFT TOP RIVET HOLE. THE CRACK STARTS AT THE TOP OF THE FITTING AND TRAVELS DOWNWARD THROUGH THE RIVET HOLE AND APPROXIMATELY .2500 FURTHER. (TC NR 20060801004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1G71 3U3  U  H2SW    E4CE                 
20060926001982006092600198NM  2006       9          26         CA060801005      120060412G291082950010141     LINE            DHAV                    DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  HYDRAULIC SYS   RUPTURED        W      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CLCLIMB          1                      CA       36205                                                          (CAN) AFTER TAKEOFF NR 1 RUDDER FULL PRESSURE AND ROLL SPOILER IB HYDRAULIC CAUTION LIGHT ILLUMINATED. CREW DECLARED EMERGENCY RETURNED TO AIRFIELD. MAINTENANCE REMOVED FLAP WELL PANEL 532AB AND FOUND AREA UNDER PANEL WAS CHARRED FROM FIRE. FIRE WAS HOT ENOUGH TO RUPTURE TWO HYDRAULIC LINES, MELTED SPACER BLOCKS AND MELTED PLASTIC ON WIRE BUNDLE. (TC NR 20060801005)                                                                                                                                                                                                                                                                                                                                                                2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060926002002006092600200EU  2006       9          26         CA060801007      120060731G2197                WIRE                                    AIRBUSA340  A340*              EU  RROYCERB211 RB211*      54555NE                              CARGO FAN       BURNED          W      K   NONE                                                                                            B  SMOKE/FUMES/ODORS/SPARKS                                                      ININSP/MAINT     1                      CA                                                                      (CAN) (FWD CARGO VENT FAULT) DISPLAYED ON ECAM. TROUBLESHOOTING IDENTIFIED BURNED WIRING UNDER FWD CARGO FLOOR, APPROX 2 IN FROM ELECTRICAL CONNECTOR 285HN-A ON FWD CARGO EXTRACTION FAN. BURNED WIRES WERE LOCATED BETWEEN SUPPORT STANDOFFS WITH NO EVIDENCE OF CHAFFING. WIRING REPAIRED IAW ESPM, REPLACED FWD CARGO EXTRACT FAN. (TC NR 20060801007)                                                                                                                                                                                                                                                                                                                                                                                      2L74 4F4  FRTA197    A12EU                
20060926002022006092600202NM  2006       9          26         CA060801008      120060708G5753734187B         TORQUE TUBE                             DHAV  DHC8  DHC8101     2809002NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  TE FLAPS        CHAFED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A LINE MAINTENANCE WALK-AROUND CHECK, AN ENGINEER FOUND THAT THE LT WING FLAP IB (SECTION BETWEEN NACELLE AND FUSELAGE) TORQUE TUBE HAS BEEN CHAFED THROUGH IN ONE SPOT BY ITS RETAINING BRACKET. TORQUE TUBE ASSY PN REPLACED WITH SERVICEABLE ASSY FUNCTIONAL TEST COMPLETED ON FLAP SYSTEM AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20060801008)                                                                                                                                                                                                                                                                                                                                                                                2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060926002032006092600203NM  2006       9          26         CA060801009      120060528G2910A44700009       ACTUATOR                                DHAV  DHC8  DHC8101     2809002NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  SERVO           LEAKING         W      E   ENGINE SHUTDOWN                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA       40236                                                          (CAN) AFTER NR 2 ENGINE START CREW OBSERVED THAT THE NR 2 HYDRAULIC SYSTEM QUANTITY HAD DECREASED TO 1 QUART. ENGINES SHUTDOWN AND PASSENGERS DISEMBARKED FOR DEFECT INVESTIGATION.  ENGINEERING DETERMINED SYSTEM FLUID LOSS TO BE FROM THE RT OB SERVO ACTUATOR HOUSING. THE SERVO ACTUATOR WAS REPLACED AND HYDRAULIC SYSTEM REPLENISHED IAW THE AMM. (TC NR 20060801009)                                                                                                                                                                                                                                                                                                                                                                    2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060926002042006092600204EU  2006       9          26         CA060802001      120060725G631035013001        FREEWHEEL UNIT                          SNIAS 350   AS350BA     8680817EU  ALLSN 250C  250C30      03013GL                              MAIN ROTOR      MAKING METAL    W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       5074 61                                                        (CAN) AFTER INSTALLING A OVERHAULED FREEWHEEL, METAL WAS FOUND (4) SEPARATE TIMES IN 61.1 HOURS, SILVER FLAKES FOUND ON CHIP PLUG. (TC NR 20060802001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1G71 3U3  UNCH9EU    E1GL                 
20060810000272006081000027NE  2006       8          10         CA060802002      220060711G72502292253850      TURBINE BLADES                          SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1        NE                              GAS GENERATOR   FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       254  254                                                       (CAN) THE PILOT SHUTDOWN THE AIRCRAFT TO HOOK UP HIS WATER BUCKET, AFTER A SHORT TIME PERIOD OF APPROXIMATELY 8 TO 10 MINUTES HE ATTEMPT TO RESTART THE AIRCRAFT. THE STARTER WOULD NOT TURN THE ENGINE. A BORESCOPE WAS USED TO LOOK INSIDE THE ENGINE AND FOUND THAT THE 1ST STAGE TURBINE BLADE HAD RUBBED. THE M03 WAS THEN REPLACED AND THE AIRCRAFT RETURN TO SERVICE. (TC NR 20060802002)                                                                                                                                                                                                                                                                                                                                                1G71 3U3  U  H9EU    E19EU                
20060926002052006092600205NM  2006       9          26         CA060802003      120060722G61207898426009      CONTROL UNIT                            DHAV  DHC8  DHC8101     2809002NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  NR 1 ENGINE     MALFUNCTIONED   W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         F  FLT CONT AFFECTED                                                             CLCLIMB          1                      CA            198                                                       (CAN) DURING THE TAKEOFF ROLL, THE FIRST OFFICER NOTED ILLUMINATION OF THE NR 1 ENGINE MANUAL CAUTION AND THE CAPTAIN ELECTED TO CONTINUE THE TAKE OFF. SHORTLY AFTER GEAR RETRACTION, THE NR 1 PROPELLER FEATHERED. THE ENGINE WAS SECURED AFTER COMPLETION OF PLATEAU HEIGHT DRILLS AND THE AIRCRAFT MANOEUVRED FOR A RETURN TO LAND.  NR 1 ELECTRONIC CONTROL UNIT REPLACED.  (TC NR 20060802003)                                                                                                                                                                                                                                                                                                                                            2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060926002062006092600206EA  2006       9          26         CA060802004      120060801G2752                WARNING MESSAGE                         CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              TE FLAPS        ILLUMINATED     W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA                                                                      (CAN) 0 FLAP LANDING DUE TO FLAP FAIL EICAS MESSAGE. ON APPROACH, CREW SELECTED FLAPS AND NOTICED THEY WERE STUCK AT ZERO.   CREW COMPLETED CHECKLIST, THEN CONTACTED DISPATCH/ MTC.   AFTER TALKING TO MTC THE FLIGHT LANDED WITH ZERO FLAP.   AIRPORT FIRE FIGHTING WAS CONTACTED AS A PRECAUTION.   FLIGHT LANDED WITHOUT INCIDENT.  MAINT RESET SYSTEM AND CARRIED OUT INSPECTION IAW TIB CRJ-27-04. SYTEM RESET OK. DMI APPILED TO HAVE FAULT CODES READ AND INTERPRETTED. (801574 8/1/2006 21:01) (TC NR 20060802004)                                                                                                                                                                                                                     2L72 4F4  FRTA21EA   E15NE                
20060926002072006092600207NE  2006       9          26         CA060802005      220060427G7320311496001       COUPLING                                DHAV  DHC8  DHC8202     2809007NM  PWA   120   PW123D      52152NE  HAMSTD14SF  14SF23      NE  RT ENGINE       WORN            W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA       182877506                                                      (CAN) DURING CRUISE, NUMBER 2 ENGINE EXPERIENCED EXTREME TORQUE FLUCTUATIONS OF UP TO 50 PRESENT WITH ASSOCIATED FUEL FLOW AND NH RPM INDICATIONS. AS A RESULT OF A SUBSEQUENT TORQUE DROP THE CREW ELECTED TO CARRY OUT A PRECAUTIONARY ENGINE SHUT DOWN IN FLIGHT.  THE NO.2 PROPELLER ASSEMBLY WAS REPLACED DUE TO THE OVERTORQUE AND SENT FOR MAJOR INSPECTION. THE MECHANICAL FUEL CONTROL UNIT (MFCU) AND FUEL PUMP WERE REPLACED DURING WHICH IT WAS DISCOVERED THAT THE INTERCONNECTING COUPLING WAS STRIPPED POSSIBLY DUE TO AN INTERNAL FAILURE OF THE MFCU. (TC NR 20060802005)                                                                                                                                                      2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060926002082006092600208NE  2006       9          26         CA060802007      220060419G7320311717503       FUEL CONTROL                            DHAV  DHC8  DHC8202     2809007NM  PWA   120   PW123D      52152NE  HAMSTD14SF  14SF23      NE  NR 1 ENGINE     FAILED          W      A   UNSCHED LANDING                                                                                 XJ ENGINE FLAMEOUT           WARNING INDICATION                                  APAPPROACH       1                      CA       20271                                                          (CAN) DURING APPROACH NR 1 ENGINE TORQUE AND RPM SURGING 10 PERCENT WITH POWER ABOVE 80 PERCENT. ENGINE SHUTDOWN AT 5000 FEET ON DOWNWIND. MAINTENANCE REPLACED NR 1 ENGINE FUEL PUMP AND FUEL CONTROL. OPERATIONAL CHECK GOOD. AIRCRAFT RETURNED TO SERVICE. (TC NR 20060802007)                                                                                                                                                                                                                                                                                                                                                                                                                                                               2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060926002092006092600209NE  2006       9          26         CA060802008      220060726G7497                WIRE            CONT                    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              MAGNETO         CHAFED          W      O   OTHER                                                                                           X  ENGINE FLAMEOUT                                                               DEDESCENT        1                      CA       400                                                            (CAN) WHEN THE COLLECTIVE LEVER WAS LOWERED DURING DESCENT FOR A LANDING AT THE HELICOPTER BASE THE ENGINE TACHOMETER BECAME ERRATIC, THE ENGINE OVERSPED ABOVE 116 PERCENT AND THE THROTTLE GOVERNOR WAS NOT WORKING. THE ROTOR TACH ALSO INDICATED AN OVERSPEED ABOVE 114 PERCENT. INSPECTION OF THE RT MAGNETO FOUND THAT THE INSULATION ON THE WIRE CARRYING THE SPEED SIGNAL FROM THE SECONDARY POINTS TO THE TACHOMETER AND SPEED GOVERNOR HAD BEEN CUT THROUGH AND SHORTED TO GROUND. THE INTERMITTENT LOSS OF SIGNAL RESULTED IN ERRATIC TACH INDICATION AND THE AIRFRAME MANUFACTURER CONFIRMED THAT WITH THAT CONDITION THE GOVERNOR COULD BE EXPECTED TO GO OFF LINE. THE MOST LIKELY CAUSE OF THE DAMAGE WAS PINCHING OF THE WIRE BE1G71 3O3  O  H11NM   1E4                  
20060913000462006091300046NM  2006       9          13         CA060802009      120060405G3240DSC252A40230    HOSE                                    DHAV  DHC8  DHC8201     2809001NM  PWA   120   PW123D      52152NE  HAMSTD14SF  14SF23      NE  BRAKES          LEAKING         W      D   RETURN TO BLOCK                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA                                                                      (CAN) DURING PRE TAKE-OFF CHECKS FOR THE FIRST FLIGHT OF THE DAY (PARK BRAKE ON), THE FLIGHT CREW NOTICED THAT THE NR 2 HYDRAULIC SYSTEM HAD LOST MOST OF ITS FLUID. AIRCRAFT GROUND RETURN AND DURING THE TAXI BACK TO THE GATE, THE NR 1 HYDRAULIC SYSTEM QUANTITY WAS ALSO OBSERVED TO BE GOING DOWN.  MAINTENANCE INSPECTION REVEALED THAT THE LT OB (NR 1) BRAKE HYDRAULIC FLEX HOSE TO BE LEAKING FLUID.  A NEW  FLEXIBLE BRAKE HOSE ASSEMBLY P/N: DSC252A4-0230 INSTALLED, BOTH HYDRAULIC SYSTEMS SERVICED AND BLEED IAW AMM (TC NR 20060802009).                                                                                                                                                                                        2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060913000502006091300050WP  2006       9          13         CA060802010      220060801G7261                ENGINE                                  FRCHLDSA227 SA227DC     3377521SW  GARRTTTPE331TPE33112UHR      WP  MCAULY4HFR344HFR34C652  NE  LEFT            LEAKING         W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA       4828                               P70275                      (CAN) ON CLIMB, THE LT LOW OIL PRESSURE LIGHT ILLUMINATED, ALONG WITH A OIL PRESSURE GAUGE DECREASE. THE LT ENGINE WAS SHUTDOWN IN FLIGHT AND RETURNED TO BASE. ON INSPECTION IT APPEARS THAT THE OIL EXITED OUT THE EXHAUST. ENGINE REMOVED AND SENT FOR REPAIR AND INSPECTION. (TC NR 20060802010)                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4T4  TRTA18SW   E4WE    6  C3PNE     
20060913000512006091300051EU  2006       9          13         CA060803001      120060614G5210852G10          SEAL                                    SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1        NE                              PAX DOOR        PEELING         W      A   UNSCHED LANDING                                                                                 D  INFLIGHT SEPARATION                                                           HOHOVERING       1                      CA                                                                      (CAN) THE PILOT WAS LONG LINING WITH THE PILOT SIDE DOORS OFF, THE WEATHER STRIPPING PEELED OFF THE DOOR FRAME. THE LAST 3 INCHES CAUGHT ON THE POCKET DOOR STOP. THE PILOT SLOWED DOWN AND LANDED TO REMOVE THE REST OF THE DOOR SEAL. THE DOOR SEAL IS 4 METERS LONG,AND ALTERNATE P/N 704A39821031.  (TC NR 20060803001)                                                                                                                                                                                                                                                                                                                                                                                                                     1G71 3U3  U  H9EU    E19EU                
20060913000542006091300054NM  2006       9          13         CA060803003      120060803G2611656020916       CONTROLLER                              BOEING727   727247      138408FNM  PWA   JT8   JT8D*            NE                              FIRE DETECTION  MALFUNCTIONED   W      F   ACTIVATE FIRE EXT.                                                                              N  FALSE WARNING                                                                 NRNOT REPORTED   1                      CA                                                                      (CAN) JUST AFTER ENGINE, ALL 3 ENGINES WERE STARTED AND THE FLIGHT CREW WERE CARRYING OUT THE AFTER START CHECKLIST, THE NR 2 ENGINE (FIRE WARNING) ILLUMINATED AND THE (FIRE BELL RANG). THE FIRE HAND WAS PULLED AND THE FIRE BOTTLE DISCHARGED LIGHT WENT OUT. MAINTENANCE CONFIRMED THAT THERE WAS NO FIRE AND THAT THE FIRE DETECTION UNIT HAD FAILED. THIS UNIT IS A ON CONDITION SOLID STATE PART. AIRCRAFT IS CURRENTLY ON THE GROUND AWAITING PARTS. (TC NR 20060803003)                                                                                                                                                                                                                                                               2L73 4F4  F  A3WE    E2EA                 
20060913000552006091300055SW  2006       9          13         CA060803004      120060728G291070061H000T13    HOSE                                    BELL  206   206L3       1182108SW  ALLSN 250C  250C30P     03013GL                              HYD SYSTEM      LEAKING         W      O   OTHER                                                                                           K  FLUID LOSS                                                                    LDLANDING        1                      CA                                                                      (CAN) UPON LANDING AND SHUTDOWN ON LAST UNEVENTFULL FLIGHT OF THE DAY. PILOT REPORTED HYD FLUID ON SIDE OF A/C. A/C GROUNDED UNTIL INSP, UPON INSP. HYD PRESSURE FEED LINE FOUND LEAKING. LINE REPLACED WITH SEVICEABLE UNIT. RECOMMEND OPERATORS AND MAINT FACILITIES INSPECT O/C HYD LINES FREQUENTLY AND REPLACE. (TC NR 20060803004)                                                                                                                                                                                                                                                                                                                                                                                                        1G71 3U3  U  H2SW    E1GL                 
20060913000582006091300058NM  2006       9          13         CA060804001      120060503G760387620136055057  CONTROL ROD                             DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF15      NE  POWER LEVER     MISINSTALLED    W      A   UNSCHED LANDING                                                                                 F  FLT CONT AFFECTED                                                             CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB NR 2 ENGINE WAS MAKING ONLY 78 PERCENT POWER AND THE ENGINE POWER LEVER WAS JAMMED 1.5 INCH FROM FULL TRAVEL.  AIRCRAFT RETURN ON GROUND SAFELY SHORTLY AFTER TAKEOFF.  MAINTENANCE FOUND NR 2 CONTROL AND CONDITION LEVER RODS HARDWARE (BOLT AND NUT) INCORRECTLY INSTALLED. PROPER HARDWARE INSTALLATION AND ENGINE RIGGING WERE PERFORMED. AN INTERNAL SAFETY ALERT WAS ISSUED ON JULY 14, 2006 IN RESPECT TO THIS EVENT. AIRFRAME HOURS: 37405:43. CYCLES:48382 (TC IN 20060804001)                                                                                                                                                                                                                                     2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060913000592006091300059EA  2006       9          13         CA060804002      120060729G3320BR95005         BALLAST                                 CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              CABIN LIGHTS    FAULTED         W      K   NONE                                                                                            B  SMOKE/FUMES/ODORS/SPARKS                                                      ININSP/MAINT     1                      CA                                                                      (CAN) DURING MAINTENANCE AN ELECTRICAL SMELL WAS APPARENT IN THE FRONT HALF OF THE CABIN.  EIGHT (8) CABIN LIGHT BALLASTS WERE FOUND AT FAULT.  ALL 8 WERE REPLACED AND AIRCRAFT WAS MONITORED FOR TWO HOURS FOR SNAG RE-OCCURENCE WITH NO FAULT FOUND.  AIRFRAME HOURS: 3602:31. CYCLES: 2780. (TC NR 20060804002)                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F4  FRTA21EA   E15NE                
20060913000612006091300061NM  2006       9          13         CA060804003      120060602G2910AN81510D        FITTING                                 DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF23      NE  NR 1 HYD SYS    FRACTURED       W      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA       310                                                            (CAN) DURING THE FLIGHT, OPERATOR LOST ALL HYDRAULIC QUANTITY AND PRESSURE FROM THE SYSTEM NR 1 AND ALL ASSOCIATED LIGHTS. CREW COMPLETED THE RESPECTIVE CHECKLIST AND LANDED WITH FLAPS 0 AND WITHOUT NORMAL BRAKING,  INVESTIGATION REVEALED THAT THE NR 1 PRESSURE MANIFOLD INLET UNION HAD FRACTURED. (TC NR 20060804003)                                                                                                                                                                                                                                                                                                                                                                                                                  2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060913000632006091300063    2006       9          13         CA060804004      420060410G3442707700301       INDICATOR                               DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF23      NE  WEATHER RADAR   MALFUNCTIONED   W      G   O2 MASK DEPLOYED                                                                                B  SMOKE/FUMES/ODORS/SPARKS                                                      DEDESCENT        1                      CA       9667 1105                                                      (CAN) DURING DESCENT, CREW DETECTED A STRONG BURNING SMELL ON THE FLIGHT DECK. FLIGHT CREW DONNED OXYGEN MASKS AND LANDED WITHOUT FURTHER INCIDENT.  FLIGHT CREW HAD REPORTED TO ENGINEERING THAT THE WEATHER RADAR WAS INOPERATIVE FROM TOP OF DESCENT. UPON INVESTIGATION BY ENGINEERING THE WEATHER RADAR INDICATOR WAS FOUND TO HAVE A STRONG BURNING SMELL. WEATHER RADAR INDICATOR REPLACED AND FUNCTIONALLY TESTED SERVICEABLE.  (TC NR 20060804004)                                                                                                                                                                                                                                                                                     2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060913000842006091300084NE  2006       9          13         CA060804005      320060329G611173030SOCN8173881SEAL                                    DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF23      NE  PROPELLER BLADE LEAKING         W      O   OTHER                                                                                           K  FLUID LOSS                                                                    CRCRUISE         1                      CA       135        200504062525                                        (CAN) DURING FLIGHT, NR 1 PROP LOST APPROXIMATELY 7 QUARTS OF OIL FROM THE HUB.  UPON ARRIVAL AIRCRAFT WAS COVERED IN OIL (LT). THERE WAS NOT AN INFLIGHT SHUTDOWN AND NO EMERGENCY MEASURES WERE REQUIRED OR TAKEN. THE AIRCRAFT RESPONDED NORMALLY.  THE PROP SEAL WAS FOUND TORN AND THE GARTER SPRING WAS DISTORTED WHERE THE TWO ENDS OF THE SPRING ARE WELDED. (TC NR 20060804005)                                                                                                                                                                                                                                                                                                                                                        2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060913001052006091300105    2006       9          13         CA060804006      420060728G61225337050         IDLER GEAR      WOODWARD                                                   PWA   PT6   PT6A67B     52043NE                              PROPELLER GOVER WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1584       13313260                                            (CAN) ENGINE PCE-PR0055 WAS SUBMITTED FOR A SCHEDULED FIRST TIME OVERHAUL (TSN 3621.0 HRS).  THE PROPELLER GOVERNOR S/N 13313260 (TSN 1583.6 HOURS) WAS DISMANTLED FOR CLEANING BEFORE OVERHAUL INSPECTION.  IT WAS DISCOVERED THAT THE IDLER GEAR BUSHING WAS SEVERELY WORN AWAY RESULTING IN AN ELLIPTICAL ROTATION OF THE GEAR THAT CAUSED THE GEAR POCKET TO WEAR IN AN OVAL MANNER ON THE PRESSURE SIDE.   A NORMAL IDLER GEAR BUSHING MEASURES APPROXIMATELY 0.100 IN.  THE WORN IDLER GEAR BUSHING MEASURED 0.0175 IN., I.E. IT HAD WORN AWAY 0.0825 IN.  IT IS NOT KNOWN WHAT CAUSED THE EXCESSIVE WEAR. THE PERIODIC OIL ANALYSIS PROGRAM (SOAP) DID NOT INDICATE A PROBLEM. AFTER DISCOVERING THIS CONDITION, WE TRIED TO ROTATE THE G       4  T          E26NE                
20061213001372006121300137EU  2006       12         13         CA060804007      120060803G2913S40             COUPLING                                SNIAS 350   AS350BA     8680817EU  TMECA ARRIELARRIEL1B    6OO30NE                              HYD PUMP        LEAKING         W      A   UNSCHED LANDING                                                                                 F  FLT CONT AFFECTED                                                             CRCRUISE         1                      CA                  40652121                                            (CAN) PILOT FELT STIFFNESS IN FLIGHT CONTROLS AND LANDED. INVESTIGATION REVEALED THAT THE SLEEVE COUPLING INTERNAL SPLINES HAD WORN EXCESSIVELY SO THAT THE FLIGHT CONTROL HYDRAULIC PUMP WAS NO LONGER DRIVEN BY THE DRIVE BELT FROM THE MAIN GREAR BOX.  THE FAILED COUPLING SHOWS SIGNS OF MILD CORROSION IN THE INTERNAL SPLINES.  THE COUPLING WAS LUBRIATED DURING THE LAST SCHEDULED INSPECTION 30 HOURS PREVIOUSLY.  THE SLEEVE COUPLING WAS REPLACED AND THE AIRCARFT WAS RETURNED TO SERVICE.   DISCUSSION WITH OTHER OPERATORS INDICATE AN INCREASE IN THE SLEEVE COUPLING FAILURE RATE SINCE THE INTRODUCTION OF THE POLY V DRIVE BELT AS REQUIRED BY AD CF-2004-10 ( SB 63.00.08) ISSUED 4 JUNE 2004.    (TC NR 20060804007)       1G71 3U3  UNCH9EU    E19EU                
20060913001132006091300113EA  2006       9          13         CA060804008      220060801G8530SLC36005F       CYLINDER HEAD                           CESSNA172   172N        2072434CE  LYC   O320  O320D2J     41508EA  MCAULY1C160 1C160DTM    GL  ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1640                                                           (CAN) ALL 4 CYLINDERS HAVE CRACKS THAT BEGIN AT THE INNER MOST EXHAUST FLANGE STUD AND MOVING TO THE EXHAUST VALVE SEAT, THEN 180 DEGREES ACROSS THE EXHAUST VALVE SEAT TO THE UPPER SPARK PLUG HOLE.  SN. E36-10511 E36-10244 E36-10426 E36-10496  NOTE: THIS MAKES 10 OF THESE CYLINDERS FROM 3 DIFFERENT AIRCRAFT IN 6 WEEKS TO HAVE THE SAME CRACKS. TIME ON THESE VARY FROM 1600 TO 2100 HOURS. ALL ON AN (ON CONDITION PROGRAM) REQUIRING AN EXTERNAL SOAPY/WATER LEAK CHECK AND BORESCOPE INSPECTION WHICH IS HOW THE DEFECT IS DISCOVERED. A CYLINDER DPI DOES NOT REVEAL AND A PARTIAL ENGINE TEARDOWN ID REQUIRED FOR VISUAL DETECTION. (TC NR 20060804008)                                                                           1H71 3O3  ONT3A12    E274    5  NP910     
20080131000132008013100013CE  2008       1          31         CA060804009      120060802G533050420066281     DOUBLER                                 BEECH 200   200BEECH    1152920CE  PWA   PT6   PT642A           NE  HARTZLHCB3T HCB3TN3     GL  FUSELAGE        DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       12559                  1129                                    (CAN)  DURING PHASE 2 INSPECTION AND WHILE PERFORMING SPECIAL INSPECTION ON NR 25 (INSPECTION OF UPPER AND LOWER WINDSHIELD CORNERS), DAMAGE TO THE DOUBLER BELOW THE WINDSCREEN WAS FOUND. THE PN OF THE DOUBLER IS 50-420066-281 LOCATED BETWEEN  FS 94.00AND FS 100.50. THE DAMAGE WAS CAUSED FROM THE ITT HARNESSES CHAFFING INTO THE DOUBLER. THE DAMAGE IS LOCATED BETWEEN 1.5 TO 5.5 LT OF THE WINDSCREEN CENTER POST, THE DOUBLER THICKNESS IS .100, THE CHAFFING DAMAGE RANGES FROM .010 TO .069 IN DEPTH. THE DAMAGED AREA HAS BEEN MAPPED, AND THE INFORMATION SENT TO MFG REPAIR DESIGN OFFICE FOR ASSESSMENT.  A FOLLOW UP REPORT SHALL BE SUBMITTED.     (TC NR 20060804009)                                                      1L72 4T4  T  A24CE   E4EA    6  CP15EA    
20060913001152006091300115WP  2006       9          13         CA060804010      120060731G6320369D25146       BEARING                                 HUGHES369   369D        4470706WP  ALLSN 250C  250C20B     03013GL                              M/R TRANSMISSIONCRACKED         W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            NRNOT REPORTED   1                      CA            574   1265                                                (CAN) 369D25146 ROLLER BEARING INNER RACE CRACKED, THIS RACE IS PRESSED ONTO TRANSMISSION T/R O/P PINION WITH AN INTERFERENCE FIT.  CRACKED INNER RACE CAUSED THE RACE TO SPALL AND CAUSED A CHIP LIGHT.  SEVERE METAL CONTAMINATION WAS FOUND (TC NR 20060804010)                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1G71 3U3  U  H3WE    E4CE                 
20060913001162006091300116CE  2006       9          13         CA060806001      120060727G3246RA105002        RIVET                                   CESSNA172   172M        2072418CE  LYC   O320  O320E2D     41508EA  MCAULY1C160 1C160DTM    GL  BRAKE LINING    SHEARED         W      O   OTHER                                                                                           O  OTHER                                                                         LDLANDING        1                      CA                                                                      (CAN) UPON LANDING THE PILOT EXPERIENCE A SEVERE PROBLEM WITH THE LT MAIN WHEEL BRAKE SYSTEM. DURING THE DISASSEMBLY OF THE LT BRAKE SYSTEM IT WAS DISCOVERED THAT THE BRAKE LINING RIVETS (RA105-002) HAD BOTH SHEARED AND THE LINING WAS NO LONGER ATTACHED TO THE BACKING PLATE.  THE RIVETS THAT SHEARED WERE MADE FROM BRASS (RA105-002) UNLIKE THE CLEVELAND RIVETS (105-002 WHICH ARE BRASS PLATED STEEL. THE AIRCRAFT WAS RETURNED TO SERVICE WITH NEW BRAKE LININGS AND NEW CLEVELAND RIVETS. (TC NR 20060806001)                                                                                                                                                                                                                      1H71 3O3  ONT3A12    E274    5  NP910     
20060913001182006091300118CE  2006       9          13         CA060807001      120060804G324616211800        WHEEL                                   CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE  MCAULY3AF34C3GFR34C703  GL  MLG             CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) APPROX 1.5 INCH CRACK AROUND CIRCUMFERENCE OF BEARING RACE, INSIDE OF WHEEL HALF, SUSPECT MIS-ALIGNMENT OF WHEEL HALF SPACER DURING BUILD-UP (TC NR 20060807001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3T3  T  A37CE   E4EA    5  CP60GL    
20060913001192006091300119EU  2006       9          13         CA060807002      120060806G6420704A33651190    BEARING                                 SNIAS 350   AS350BA     8680817EU                                                               TAIL ROTOR      NOISY           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       200                                                            (CAN) FOUND DURING 500 HOUR INSPECTION.  ABNORMAL BEARING NOISE, AXIAL WEAR BEYOND LIMITS. (TC NR 20060807002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1G71 3U    NCH9EU                         
20060913001212006091300121EU  2006       9          13         CA060808001      120060731G29109740926112      RELAY                                   PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  HYD SYSTEM      MALFUNCTIONED   W      O   OTHER                                                                                           J  WARNING INDICATION                                                            LDLANDING        1                      CA       3988 3988                                                      (CAN) LANDING GEAR SELECTED DOWN ON FINAL. NO GEEN DOWN LOCK INDICATION FOR THE NOSE GEAR. PILOT DID AN EMERGENCY GEAR EXTENSION AND GOT THE LANDING GEAR DOWN AND LOCKED INDICATION FOR ALL THREE GEAR. THE SYSTEM WAS TROUBLESHOT AND FOUND TO HAVE A MALFUNCTIONING HYD PWR RELAY K601. THE RELAY WAS REPLACED AND A FUNCTIONAL CHECK OF THE LANDING GEAR SYSTEM WAS CARRIED OUT WITH NO FURTHER PROBLEMS. (TC NR 20060808001)                                                                                                                                                                                                                                                                                                               1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20060913001222006091300122EA  2006       9          13         CA060808004      220060703G8520LW13521         BEARING                                 ROBSINR44   R44         7640120WP  LYC   O540  O540F1B5    41532EA                              CONNECTING ROD  BROKEN          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       2183 2183                                                      (CAN) CONNECTING ROD BEARINGS ON NR 1,3, AND 5 RODS HAD SIGNIFICANT SURFACE DELAMINATION.  BROKEN PIECES .5 INCH L X .1250 INCH W FOUND IN BETWEEN CONNECTING ROD BEARING AND CRANKSHAFT. (TC INCH 20060808004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1G71 3O3  O  H11NM   E295                 
20060913001232006091300123GL  2006       9          13         CA060808005      220060719G723023056109        SCROLL          ALLSN                   BELL  206   206L1       1182107SW  ALLSN 250C  250C28      03013GL                              COMPRESSOR      CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA       6983       CAC70614                                            (CAN) HIGH TOT WAS NOTICED IN CRUISE. ON RETURNING A POWER CHECK WAS CARRIED OUT AND LOW POWER WAS DETECTED. A HAIT LINE CRACK WAS IDENTIFIED BY VISUAL INSPECTION  IN THE ELBOW AREA OF SCROLL. COMPRESSOR CHANGED. (TC NR 20060808005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1G71 3U3  U  H2SW    E1GL                 
20060913001252006091300125CE  2006       9          13         CA060808006      120060804G534312116011        FITTING                                 CESSNA206   U206B       2073322CE  CONT  O520  IO520D      17032SO  MCAULY3A32C D3A32C90    GL  MLG OUTBOARD    CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       9713                                                           (CAN) DURING A 100 HOUR INSPECTION LOOSE RIVETS WERE NOTICED AROUND THE LT MAIN GEAR.  ONCE THE FLOOR WAS LIFTED TO PERFORM THE REPAIRS, THE LT MAIN GEAR OB FITTING WAS FOUND TO BE CRACKED PROPOGATING FROM THE AFT END OF THE GEAR LEG OPENING TOWARDS THE AFT END OF THE FITTING. (TC NR 20060808006)                                                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3O3  O  A4CE    E5CE    5  CP21EA    
20060913001262006091300126WP  2006       9          13         CA060808009      120060703G3213369H600151      STRUT                                   HUGHES369   369D        4470706WP  ALLSN 250C  250C20B     03013GL                              MLG             CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING THE YEARLY INSPECTION, THE LT AFT LANDING GEAR STRUT WAS INSPECTED AND FOUND TO BE CRACKED, FROM THE LOWER DRAG BRACE ATTACH HOLE.  THE CRACK WAS APPROX. 1.250 INCH LONG, AND EXTENDED LENGTHWISE TOWARDS THE BEND IN THE STRUT (TC NR  20060808009)                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1G71 3U3  U  H3WE    E4CE                 
20060913001322006091300132EA  2006       9          13         CA060808010      120060710G5610601R3303317     WINDSHIELD                              CNDAIRCL600 CL6002C10   1390015EA  GE    CF34  CF348C1          NE                              COCKPIT         CRACKED         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      CA       3949                                                           (CAN) (ENROUTE, CREW SENT ACARS MESSAGE TO DISPATCH THAT THEY HAD A BROKEN CAPTAINS WINDSHIELD, AND WERE DIVERTING) MX DISPATCHED WITH WINDSHIELD.  WINDSHIELD REPLACED. (TC NR 20060808010)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F4  FRTA21EA   EOOO63EN             
20060913001472006091300147NE  2006       9          13         CA060808011      220060204G7200CF343A1         ENGINE                                  CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              RIGHT           MALFUNCTIONED   W      E   ENGINE SHUTDOWN                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  DEDESCENT        1                      CA                                                                      (CAN) EXPERIENCED THE RT ENGINE IFSD, JUST AFTER THE LIGHTNING STRIKE TODAY.   PIC DID NOT TRY TO RESTART THE ENGINE DURING THE FLIGHT, BUT AFTER THE LANDING WE COULD START THE ENGINE.  THERE IS NO VISIBLE DAMAGE ON THE OUTSIDE OF THE ENGINE, WE WILL DO THE BSI.  WE WOULD LIKE TO KNOW THE MOST PROBABLE ROOT CAUSE OF THE IFSD.  IF YOU HAVE A SIMILAR EXPERIENCE IN OTHER OPERATORS, PLEASE PROVIDE YOUR INFORMATION. THE CIRCUMSTANCES IS AS FOLLOWS, OCCURRED DATE : APRIL 02, 10:37JST  ASN: 7052 ESN : 807222 FLT PHASE : DURING THE DESCENDING TO DESTINATION ALT : 13,000 FT IGNITION : CONTINUOUS IGNITION WEATHER CONDITION : IN-CLOUD, LIGHT RAIN) AFTER THE EVENT THE OPERATOR SUPPLIED THE DFDR TO MFG.  MFG ANALYSIS CONCLU2L72 4F4  FRTA21EA   E15NE                
20060913001482006091300148SW  2006       9          13         CA060809001      120060809G29102781006019      LINE                                    SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE33111U   01514WP  MCAULY4HFR344HFR34C652  NE  HYDRAULIC SYSTEMLEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) FOUND HYD LEAK IN LT WHEEL WELL.  GEAR UP LINE FOUND CRACKED.  LINE REPLACED, GEAR SWINGS CARRIED OUT.  AIRCRAFT RETURNED TO SERVICE (TC NR 20060809001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4T4  TRTA8SW    E4WE    6  C3PNE     
20060913001492006091300149SO  2006       9          13         CA060809002      120060528G7810LW121127        EXHAUST DUCT                            PIPER PA31  PA31325     7103105SO  LYC   O540  TIO540F2BD  41532EA  HARTZLHCE3Y HCE3YR2A    GL  ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1599                                                           (CAN) EXHAUST TRANSITION BETWEEN TURBO AND EXHAUST STACKS FROM CYLINDERS HAD CRACKED AND STARTED TO BLOW A HOLE BELOW THE EGT PROBE HOLE. THE DEFECT WAS NOTICED BY AN EXHAUST STAIN ON THE INSIDE OF THE COWL ON A MAINTENANCE DAILY INSPECTION. THE AIRCRAFT WAS 39 HOURS OUT OF INSPECTION. (TC NR 20060809002)                                                                                                                                                                                                                                                                                                                                                                                                                              1L72 3O3  O  A20SO   E14EA   5  CP33EA    
20061018000782006101800078NM  2006       10         18         CA060810001      120060810G5220MS2764639       ROD END                                 DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF15      NE  EMERGENCY EXIT  SEIZED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A C-CHECK INSPECTION THE TASK WAS CALL UP TO INSPECT THE FWD EMERGENCY EXIT. UPON INSPECTION IT WAS DETERMINED THAT IT WAS EXTREMELY STIFF AND DIFFICULT TO OPERATE. UPON REMOVAL AND TROUBLESHOOTING IT WAS DETERMINED THAT THE CONNECTING ROD END (X10) REF IPC 52-20-00 FIG. 20 ITEM 180 WERE FOUND SEIZED INTERNALLY. THE FAILURE APPEARS TO BE DUE THE PHENOLIC BALL WIPER NOT ALLOWING THE BEARING TO ROLL FREELY. IT WAS ALSO DETERMINED THAT THE LAYSHAFT BEARINGS (X4) EXHIBITED ABNORMAL WEAR AND CORROSION ASSOCIATED WITH HIGH TIME BEARINGS REF IPC 52-20-00 FIG. 20 ITEM 590. 2 OF THE 4 HAVE FAILED DUE TO INTERNAL SEIZING. ALL PART ARE CURRENTLY BEING REPLACED.                                                 2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060913001502006091300150CE  2006       9          13         CA060810004      120060731G5712052303018       RIB                                     CESSNA172   172M        2072418CE  LYC   O320  O320E2D     41508EA  MCAULY1C160 1C160DTM    GL  LT WING         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       19931                                                          (CAN) DURING NR 3 INSPECTION CRACK LOCATED IN (D) RIB JUST OB OF WING STRUT. LT WING. (TC NR 20060810004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3O3  ONT3A12    E274    5  NP910     
20060913001512006091300151CE  2006       9          13         CA060810005      120060806G77121013890053      TRANSMITTER                             BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA  HARTZLHCD4N3HCD4N3A     GL  TORQUE          FAILED          W      C   ABORTED TAKEOFF                                                                                 N  FALSE WARNING                                                                 TOTAKEOFF        1                      CA                                                                      (CAN) ON TAKEOFF RT TORQUE TRANSMITTER WAS READING HIGH AIRCRAFT RETURNED AIRPORT. AIRCRAFT ELECTRICAL POWER TURNED OFF AND TORQUE INDICATOR WENT TO ZERO. A GROUND RUN WAS ACCOMPLISHED AND TORQUE INDICATION WAS NORMAL AT HIGH AND LOW POWER SETTINGS. AIRCRAFT RETURNED TO DESTINATION WITHOUT FURTHER INCIDENT.  MAINTENANCE REPLACED RT ENGINE TORQUE TRANSMITTER P/N 101-390005-3 AS A PRECAUTIONARY. (TC NR 20060810005)                                                                                                                                                                                                                                                                                                                1L72 4T4  T  A24CE   E4EA    5  CSTC      
20060913001522006091300152SO  2006       9          13         CA060810006      120060726G552311030120115     SUPPORT                                 EMB   110   EMB110P1    3260122SO  PWA   PT6   PT6A34      52043EA  HARTZLHCB3T HCB3TN3     GL  BALANCE WEIGHT  CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) WHILE DOING AN INSPECTION OF THE LTO ELEVATOR AND ITS ASSOCIATED PARTS A CRACK WAS FOUND IN THE ELEVATOR BALANCE WEIGHT SUPPORT. THE CRACK MEASURED   2.3750 OF AN INCH IN LENGTH AND STARTED APPROXIMATELY 2 INCHES BELOW THE LOWER THROUGH-TUBE FOR THE BALANCE SUPPORT TO ELEVATOR TORQUE TUBE ATTACH POINTS. THE SUPPORT WAS REPLACED WITH A NEW ONE. (TC NR 20060810006)                                                                                                                                                                                                                                                                                                                                                             1L72 4T4  T  A21SO   E4EA    6  CP15EA    
20060913001532006091300153EU  2006       9          13         CA060810007      120060726G2740HC273H0344      ARM                                     BAC   146   146200A     1500266EU  LYC   ALF502ALF502R5    41580NE                              LEVER           FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       3626114                                                        (CAN) RESTRICTED MOVEMENT OF CONTROL COLUMN IN THE AFT DIRECTION. SEE CA1673 14 NR CTS/06/001 ATTACHED (TC NR 20060810007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2H74 4F4  F  A49EU   E6NE                 
20060913001542006091300154SO  2006       9          13         CA060811001      120060807G2400                PANEL                                   PIPER PA31  PA31P       7103120SO  LYC   O541  TIGO541E1A  41539EA  HARTZLHCC3Y HCC3YN      GL  CIRCUIT BREAKER SMOKE           W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA                                                                      (CAN) CIRCUIT BREAKER PANEL STARTED TO SMOKE AND SPARK DURING CRUISE AT 14000 FT. ELECTRICAL FIRE CHECKLIST WAS INITIATED AND DESCENDED TO 7500 FT. UPON COMPLETION OF ELECTRICAL FIRE CHECKLIST SMOKE AND SPARK NO LONGER PRESENT.  (TC NR 20060811001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L72 3O3  O  A8EA    E19EA   5  CP25EA    
20060913001552006091300155WP  2006       9          13         CA060811002      120060810G7921369D25623       BELT                                    HUGHES369   369D        4470706WP  ALLSN 250C  250C20B     03013GL                              BLOWER OIL COOL WORN            W      O   OTHER                                                                                           O  OTHER                                                                         DEDESCENT        1                      CA       816                                                            (CAN) ON APPROACH TO LAND THE PILOT HEARD A NOISE TO THE REAR OF THE AIRCRAFT FOLLOWED BY A VIBRATION.  UPON INSPECTION THE ENGINEER NOTICED THE OIL COOLER BLOWER BELT TENSION WAS LOOSE AND THE TEETH OF THE BELT WERE WORN. (TC NR 20060811002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1G71 3U3  U  H3WE    E4CE                 
20061018000792006101800079NM  2006       10         18         CA060811003      120060810G3297471515          WIRE HARNESS                            BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  NLG WOW         DAMAGED         W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) LANDING GEAR DID NOT RETRACT AFTER TAKE OFF, RETURN TO FIELD. FOUND FAULTY NLG WOW 2/ CENTERING HARNESS. HARNESS REPLACED. AIRCRAFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
20061213001382006121300138SW  2006       12         13         CA060814002      120060717G6220412010190105    SPINDLE         BELL                    BELL  412   412         1182202SW                                                               MAIN ROTOR HUB  DEBONDED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2396       A2713                                               (CAN) ON A MAIN ROTOR HUB ASSY 2500 HOUR INSPECTION THE RED BLADE SPINDLE ASSY WAS FOUND WITH DAMPER BEARING DEBONDED. (TC NR 20060814002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G72 4U      H4SW                         
20061018000802006101800080GL  2006       10         18         CA060814003      320060729G61106505656         BRUSH BLOCK                             LKHEED188   188LKHEED*         WP  ALLSN 501D  501D13      03004GL  ALLSN A6441 A6441FN606  GL  NR 2 PROPELLER  DAMAGED         W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) AFTER TAKEOFF CREW NOTICED NR 2 BETA LIGHT ILLUMINATED AND PROP RPM ERRATIC THE CREW ELECTED TO SHUT-DOWN NR 2 ENG. AND RETURN TO BASE FOR MAINTENANCE. BRUSH BLOCK WAS CHANGED ENG. WAS GROUND RUN  AND FOUND SERVICABLE. (TC NR 20060814003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L74 4T4  T  4A22    E282    6  CP898     
20060913001662006091300166SW  2006       9          13         CA060815001      120060807G29102781032167      LINE                                    SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE33111U   01514WP  MCAULY4HFR344HFR34C652  NE  HYDRAULIC SYS   CRACKED         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) HYDRAULIC FLUID NOTICED BY MAINTENANCE ON BELLY AREA OF AIRCRAFT.  GEAR UP LINE FOUND CRACKED.  LINE REPLACED AND GEAR SWINGS CHECKED SERVICIBLE. (TC NR 20060815001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4T4  TRTA8SW    E4WE    6  C3PNE     
20061018000812006101800081NM  2006       10         18         CA060815002      120060814G522085220270001     MECHANISM                               DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF15      NE  EMERGENCY EXIT  SEIZED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3786337863                                                     (CAN) DURING INTERNALLY GENERATED MAINTENANCE FLEET CAMPAIGN TO CHECK FOR EMERGENCY DOOR OPERATING FORCE. MAINTENANCE UNABLE TO OPEN FORWARD EMERGENCY EXIT DOOR USING INTERNAL OR EXTERNAL HANDLE ( TASK 5220/07). REQUIRED DISASSEMBLY OF DOOR OUTER SHAFT MECHANISM TO ALLOW DOOR TO BE REMOVED. DISASSEMBLY OF OUTER SHAFT HANDLE FOUND BURR OF METAL ON SHAFT. DOOR REPAIRED AND MECHANISM LUBRICATED. AIRCRAFT HAD ACCUMULATED 1023HR/1823CY SINCE LAST SCHEDULED ACCOMPLISHMENT OF TASK 5220/07 IN JAN2006.                                                                                                                                                                                                                              2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060913001682006091300168SW  2006       9          13         CA060815003      120060815G79312090620031      PRESSURE SWITCH                         BELL  212   212         1181420SW  PWA   PT6T  PT6T3       52045EA                              ENGINE OIL      LEAKING         W      O   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      CA       296                                                            (CAN) FLUID LEAK AT UNION OF SWITCH BODY.  THE BODY NORMALY HAS A RIVET TO KEEP THE UNIT FROM BEING TAKEN APART, BUT THIS RIVET WAS FOUND TO BE MISSING.  THE THREADS HAD DAMAGE WHERE THE RIVET HOLE WAS.  A HOLE IS PROVIDED IN THE THREADS TO INSTALL A RIVET.  THIS DID NOT LINE UP. (TC NR 20060815003)                                                                                                                                                                                                                                                                                                                                                                                                                                    1G71 4U4  U  H4SW    E22EA                
20060913001722006091300172WP  2006       9          13         CA060815004      120060815G801131B22111        STARTER                                 ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              ENGINE          BROKEN          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       25                                                             (CAN) PILOT WENT TO START THE AIRCRAFT.  HE COULD HEAR THE MOTOR TURNING, HOWEVER THE ENGINE WAS NOT TURNING OVER.  THE AME FOUND THE DRIVE TO BE ENGAGED TO THE RING GEAR.  WHEN THE STARTER WAS REMOVED, THE DRIVE COULD BE TURNED FREELY BY HAND.  THE DRIVE FAILED INTERNALLY.  NO REPORT OF ANY BACKFIRE OR KICKBACK DURING START. THE AME BELIEVES THAT AN INTERRUPTION OF THE POWER TO THE STARTER MAY HAVE CAUSED THE STARTER TO DISENGAGE AND REENGAGE, DAMAGING THE STARTER PINION.  HE BELIEVES THE FAULT TO BE IN THE AIRCRAFT WIRING, NOT IN THE STARTER.  (TC NR 20060815004)                                                                                                                                                     1G71 3O3  O  H11NM   1E4                  
20070516001652007051600165NE  2007       5          16         CA060816001      220060815G7261                OIL SYSTEM                              BOEING767   767233      1385113NM  PWA   JT9   JT9D7R4D    52054NE                              ENGINE          LOW PRESSURE    W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA       4595                                                           (CAN) ENGINE INFLIGHT SHUTDOWN DO TO OIL PRESSURE AND QUANTITY LOSS, ENROUTE, DIVERTED, SUSPECT NR 4 BEARING. (TC NR 20060816001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F4  FRTA1NM    E3NE                 
20061018000822006101800082NM  2006       10         18         CA060816002      120060707G528083231044005     GUARD                                   DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF15      NE  RT NACELLE      DAMAGED         W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB, AFTER GEAR UP SELECTION AMBER AND RED LIGHTS ILLUMINATED IN GEAR HANDLE, ALONG WITH 3 AMBER LANDING GEAR DOOR LIGHTS. A LOUD GRINDING NOISE WAS HEARD IN THE COCKPIT. AIRCRAFT RETURNED AND LANDED SAFELY TO THE ORIGINATING AIRPORT. MAINTENANCE FOUND RT NACELLE`S WHEEL WELL DEBRIS GUARD DAMAGED AND WAS REPLACED. NO MAINTENANCE WAS PREVIOUSLY PERFORMED IN THAT AREA. MAINTENANCE FEED-BACK REVEALED THAT THE DEBRIS GUARD GETS LOOSE QUITE OFTEN, DUE TO THE FASTENING SYSTEM USED. AIRFRAME HOURS WERE: 36610:07. CYCLES WERE: 40842. (TC NR 20060816002)                                                                                                                                                          2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060913001732006091300173EA  2006       9          13         CA060816003      120060809G492038004883        APU                                     CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                                              SMOKE           W      O   OTHER                                                                                           KB FLUID LOSS                SMOKE/FUMES/ODORS/SPARKS                            NRNOT REPORTED   1                      CA       1592815928                                                     (CAN) AT THE GATE, CREW TURNED ON BOTH AIR CONDITIONING PACKS AND SMOKE/AND OR HAZE ACCOMPANIED BY ODOR BEGAN TO FILL THE COCKPIT AND CABIN. CREW IMMEDIATELY OPENED THE MAIN CABIN DOOR TO VENT THE AREA, AND SMOKE/HAZE BEGAN TO DISSIPATE. MAINTENANCE FOUND A MAJOR OIL LEAK FROM THE COMPRESSOR SECTION OF THE APU. OIL WAS INJESTED IN TO ONE OR BOTH PACKS. NEW APU INSTALLED. BOTH CONDENSOR BAGS REPLACED AND DUCTS CLEANED OF OIL. INFORMATION WILL BE UPDATED WHEN ROOT CAUSE OF LEAK IS AVAILABLE. (TC NR 20060816003)                                                                                                                                                                                                              2L72 4F4  FRTA21EA   E15NE                
20060913001912006091300191NE  2006       9          13         CA060816004      220060701G7230                COMPRESSOR                              SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1        NE                              ENGINE          MALFUNCTIONED   W      E   ENGINE SHUTDOWN                                                                                 E  VIBRATION/BUFFET                                                              TXTAXI/GRND HDL  1                      CA       3745 1396                                                      (CAN) PILOT STARTED THE AIRCRAFT IN THE FIELD AND NOTICED THE THE START WAS VERY SLOW, HE RETURNED FROM A FLIGHT AND NOTIFIED THE MAINTENANCE STAFF OF THE PROBLEM. THEY HAD THE PILOT START THE AIRCRAFT AND NOTICED THAT THE ENGINE WAS VIBRATING, THEY MADE THE PILOT ABORT THE START. UPON FURTHER INVESTIGATION THEY MOTORED OVER THE ENGINE WITHOUT STARTING IT AND THERE WAS A SCREACHING GRINDING NOISE COMING FROM THE ENGINE. THEY INSPECTED THE STARTER GENERATOR AND CHECKED THE ENGINE AND DRIVE SHAFT FOR CONDITION BUT DIDN`T FIND ANYTHING. THEY HAND ROTATED THE POWER TURBINE BLADES AND THERE WASN`T ANY NOISE. THEY ROTATED THE COMPRESSOR AND DISCOVERED THAT THERE WAS RUBBING NOISE COMING FROM THE M03. THE ENGINE WAS R1G71 3U3  U  H9EU    E19EU                
20070516001662007051600166NM  2007       5          16         CA060816005      120060815G7600                BEARING                                 DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF15      NE  CONDITION CABLE SEIZED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3733137331                                                     (CAN) DURING ROUTINE MAINTENANCE INSPECTION OF MFG TASK 422 (A CHECK 500 HR REPETITIVE TASK) ZONAL  INSPECTION OF RT ENGINE COMPARTMENT. FOUND POWER AND CONDITION CABLE PULLEYS (2 EACH SYSTEM, TOTAL 4 PULLEYS) IN THE UPPER AFT NACELLE/FRONT OF WING SPAR, TO ALL HAVE SEIZED BEARINGS (1 PULLEY WITH BRG ASSY FALLING OUT OF PHENOLIC PULLEY). PULLEYS REPLACED AND ENGINE CONTROLS RE-RIGGED. AIRCRAFT HAD ACCUMULATED 492 HOURS SINCE LAST ACCOMPLISHMENT OF TASK 422, AND 2465 HOURS SINCE LAST ACCOMPLISHMENT OF TASK 7610/05 (C-CHECK 5500 HR TASK) VISUAL INSPECTION OF ENGINE POWER AND CONDITION CONTROL CABLES AND PULLEYS. (TC NR 20060816005)                                                                                   2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20061018000842006101800084SO  2006       10         18         CA060816006      120060815G5330                SKIN                                    PIPER PA31  PA31350     7103110SO  LYC   O540  TIO540J2BD  41532EA  HARTZLHCE3Y HCE3YR2A    GL  FUSELAGE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) WHILE DOING A MOD TO THE AIRCRAFT THE ELT ANTENNA HAD TO BE REMOVED. THE AIRCRAFT SKIN WAS FOUND TO BE CRACKED ON 2 SIDES OF THE ANTENNA. THE ANTENNA HAD NOT BEEN MOUNTED PROPERLY. (TC NR 20060816006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L72 3O3  O  A20SO   E14EA   5  CP33EA    
20060913001922006091300192GL  2006       9          13         CA060817001      220060710G7320AN4H12A         BOLT                                    CVAC  STC   STC3405800         WP  ALLSN 501D  501D13D     03004GL  ALLSN A6441 A6441FN606  GL  NR 2 FUEL       WORN            W      E   ENGINE SHUTDOWN                                                                                 F  FLT CONT AFFECTED                                                             DEDESCENT        1                      CA                                                                      (CAN) THIS REPORT IS A FOLLOW-UP TO THE ORIGINAL VERBAL REPORT MADE IMMEDIATELY AFTER THE INCIDENT. THE AC LOST CONTROL OF THE NR 2 FUEL COORDINATOR AT THE TOP OF THE DECENT INTO YVR.  THE (E) HANDLE WAS PULLED ON THE NR 2 ENGINE 5 MILES BACK FROM THE YVR APPROACH AND THE AIRCRAFT LANDED SAFELY. ON EXAMINATION WE DISCOVERED THAT THE PINCH BOLT THAT HOLDS THE FUEL COORDINATOR ONTO THE NOTCH IN A SPLINED SHAFT HAD WORN TO A POINT THAT THE COORDINATOR ARM CAME ADRIFT FROM THE FUEL COORDINATOR. WE HAVE CARRIED OUT A FLEET WIDE CAMPAIGN DIRECTIVE CHECKING ALL OUR IN-SERVICE CONVAIRS FOR BOLT CONDITION AND THREAD DAMAGE. WE REPLACED 9 OUT OF 14 BOLTS DUE TO SLIGHT WEAR, AS A PRECAUTION. (TC NR 20060817001)           2L72 4T4  TRT6A6     E282    6  CP898     
20060913001942006091300194CE  2006       9          13         CA060817002      120060328G2432S35979          SENSOR                                  CESSNA500   560CESSNA   2076750CE  PWA   530   PW535A           NE                              BATTERY         FAILED          W      O   OTHER                                                                                           N  FALSE WARNING                                                                 CRCRUISE         1                      CA       573                                                            (CAN)  INTERMITTENT FAILURE OF TEMPERATURE SENSOR CAUSING INDICATED OVERTEMP OF AIRCRAFT MAIN BATTERY FOR SEVERAL SECONDS AT A TIME IN FLIGHT CAUSING MASTER CAUTION WARNING LIGHT ALSO.  REPLACED TEMPERATURE SENSOR, SYSTEM CHECKED OK.  NOTE THIS IS SECOND SENSOR TO FAIL IN 1284 HOURS. (TC NR 20060817002)                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F4  FRTA22CE   E00053EN             
20060913001972006091300197CE  2006       9          13         CA060817003      120060501G783025630005        SEAL            PARKERHANFIN            CESSNA500   560CESSNA   2076750CE  PWA   530   PW535A           NE                              T/R ACTUATOR    LEAKING         W      O   OTHER                                                                                           K  FLUID LOSS                                                                    TXTAXI/GRND HDL  1                      CA       1385       1559                                                (CAN) IB THRUST REVRSER ACTUATOR LEAKING HYDRAULIC FLUID, GETTING PROGRESSIVELY WORSE, LEAKING FLUID TRAIL ON TR STANG.   IB STANG CANNOT BE REMOVED MAKING DIAGNOSIS OF PROBEM DIFFICULT.   REPLACED IB T/R ACTUATOR WITH OVERHAULED UNIT WHICH REQUIRED ENGINE TO BE REMOVED FROM THE AIRCRAFT.   (TC NR 20060817003)                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRTA22CE   E00053EN             
20060913001982006091300198NE  2006       9          13         CA060817004      220060518G7532305265501       GASKET                                  CESSNA500   560CESSNA   2076750CE  PWA   530   PW535A           NE                              BLEED VALVE     BROKEN          W      O   OTHER                                                                                           R  PARTIAL RPM/PWR LOSS                                                          CRCRUISE         1                      CA       1390                                                           (CAN) ENGINE AT TAKEOFF AND CRUISE AT 40,000 FT AND ABOVE REQUIRED N2 TO BE HIGHER BY 1 - 1.5 PERCENT HIGHER THAN NORMAL FOR A SPECIFIC N1.   PROBELEM FOUND TO BE A COMPRESSOR BLEED VALVE NOT CLOSING COMPLETELY.  PROBLEM CAUSED BY LEAKING (BROKEN) GASKET BETWEEN COMPRESSOR BLEED VALVE AND BLEED VALVE SERVO (TORK MOTOR).  (TC NR 20060817004)                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA22CE   E00053EN             
20060913002002006091300200CE  2006       9          13         CA060817005      120060619G251001073370        INERTIA REEL    PACIFICSCIEN            CESSNA500   560CESSNA   2076750CE  PWA   530   PW535A           NE                              SEAT BELT       BROKEN          W      O   OTHER                                                                                           W  INADEQUATE Q C                                                                CRCRUISE         1                      CA                                                                      (CAN) COPILOT SHOULDER HARNESS (JAMS) WHEN EXTENDING:  FOUND PLASTIC END COVER OF INERTIA REEL BROKEN LOOSE, CAUSING INTERIM REEL TO MALFUNCTION. CAUSED BY COPILOT PUTTING FLIGHT MANUALS ETC BEHIND SEAT AND PUSHING SEAT AFT ON SEAT RAILS WHICH PUSHED SEAT BOTTOM SKIRT INTO INERTIA REEL.  - THIS IS TO BE CORRECTED BY EDUCATING THE (PILOTS) TO THE CAUSE OF THE PROBLEM AND THE REPLACEMENT OF THE INERTIA REEL.  (TC NR 20060817005)                                                                                                                                                                                                                                                                                                  2L72 4F4  FRTA22CE   E00053EN             
20060913002402006091300240EA  2006       9          13         CA060817006      220060804G8530ST203           RING                                    PIPER PA23  PA23250     7102308SO  LYC   O540  TIO540C1A   41532EA  HARTZLHCE2Y HCE2YR2     GL  CYLINDER        DELAMINATED     W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       506  506   104593                                              (CAN) THE TECHNICIANS OBSERVED AN ABNORMAL LOSS OF COMPRESSION ON SOME CYLINDERS FOLLOWING A ROUTINE INSPECTION. THEY REMOVED THE CYLINDERS AND SENT THEM TO OUR SHOP FOR INVESTIGATION. WE OBSERVED A DELAMINATION OF CHROME PLATING ON THE CYLINDER RINGS. WE REPAIRED THE CYLINDERS BY REPLACING THE DEFECTIVE PARTS WITH A NEW PARTS. THE MANUFACTURER HAS BEEN ADVISED ABOUT THE DEFECTIVE RINGS.  (TC NR 20060817006)                                                                                                                                                                                                                                                                                                                     1L72 3O3  O  1A10    E14EA   5  CP9EA     
20060913002532006091300253EA  2006       9          13         CA060817007      220060817G8520                BEARING                                 PIPER PA31  PA31350     7103110SO  LYC   O540  TIO540J2BD  41532EA  HARTZLHCE3Y HCE3YR2A    GL  CRANKSHAFT      DAMAGED         W      K   NONE                                                                                            KB FLUID LOSS                SMOKE/FUMES/ODORS/SPARKS                            ININSP/MAINT     1                      CA            2209                          L793261A                    (CAN) PILOTS NOTICED SMOKE COMING FROM THE LT ENGINE AFTER SHUTDOWN. THEY ALSO NOTICED AN OIL LEAK. FURTHER INVESTIGATION REVEALED THAT ONE CRANKSHAFT BEARING HAD BEEN MOVED FROM ITS ORIGINAL PLACE AND WAS NOW LOOSE. THE ENGINE IS BEING REMOVED FOR REPLACEMENT. A TEARDOWN REPORT WILL BE REQUESTED. (TC NR 20060817007)                                                                                                                                                                                                                                                                                                                                                                                                                  1L72 3O3  O  A20SO   E14EA   5  CP33EA    
20061018000852006101800085NM  2006       10         18         CA060818001      120060803G29102890410115      LINE                                    DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE                              HYD SYSTEM      CRACKED         W      O   OTHER                                                                                           K  FLUID LOSS                                                                    CRCRUISE         1                      CA       33559                                                          (CAN) HYD LINE IN UPPER FORWARD AREA OF NR 1 NACELLE CHAFED THROUGH AT ADJACENT ADELE CLAMP,  LEAKAGE LOCATED AND LINE ASSY P/N 82970410-115 REPLACED, SYSTEM BLED AND REPRESSURIZED WITH NO FURTHER FAULTS. GOING THROUGH THE LAST 1 MONTH PERIOD THERE HAVE BEEN NO RELATED DEFECTS IN REGARDS TO ATA 29 ON THIS A/C. THIS WAS AN ISOLATED INCIDENT NOT A RECURRING DEFECT.  NO SDR IS REQUIRED OR SUBMITTED. LAST SCHEDULED INSP WAS THE DAILY INSP OF AUG 3 /06 AT TTAF 33549.3 HRS CURRENT TTAF ON A/C 33559.7 HRS. NEXT INSP, DAILY INSP DUE AUG 4 2006 L CHECK AUG 8 2006. (TC NR 20060818001)                                                                                                                                           2H72 4T4  TRTA13NM   E20NE                
20061018000862006101800086SW  2006       10         18         CA060818002      120060817G5300S3526EC4        WASHER                                  BELL  407   407         1182206SW                                                               ECU             DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN)  THE -4 WASHER IS NOT CUT TO FIT THE BOLT AT THE SHANK, CAUSING FRETTING AND CORROSION ON THE SHANK RADIUS UNDER THE BOLT HEAD.   (TC NR 20060818002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1G71 3U    O H2SW                         
20060913002542006091300254SW  2006       9          13         CA060818003      120060803G5302407530014101    SKIN                                    BELL  407   407         1182206SW  ALLSN 250C  250C47B          GL                              TAILBOOM        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1700                                                           (CAN) DURING SCHEDULED 150 HOUR TAILBOOM INSPECTION A CRACK MEASURING .7500 OF AN INCH LONG WAS DISCOVERED ON THE UPPER LT SIDE OF THE TAILBOOM AT STATION 98.89. AIRCRAFT WAS GROUNDED AND A NEW TAILBOOM WAS ORDERED (200 SERIES). (TC NR 20060818003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1G71 3U3  UO H2SW    E1GL                 
20061018000872006101800087SW  2006       10         18         CA060818004      120060814G6720UK              BOLT                                    BELL  204   204B        1181404SW  LYC   T53   T5311B      41549NE                              TAIL ROTOR      LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A 100 HOUR INSPECTION THE ENGINEER NOTED A LARGE AMOUNT OF PLAY IN THE CLEVIS OF THE TAIL ROTOR FLIGHT CONTROL ROD.  INVESTIGATION REVEALED AN UNDERSIZED BOLT , IE SMALLER DIAMETER,  WAS INSTALLED.  THE CORREECT BOLT, P/N AN175-20 WAS INSTALLED AND A FUNCTION CKECK CARRIED OUT, WITH NO FAULT FOUND.  AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060818004)                                                                                                                                                                                                                                                                                                                                                                 1G71 4U4  U  H1SW    E1EA                 
20060913002552006091300255GL  2006       9          13         CA060818005      220060816G72306887167         CASE            ALLSN                   BELL  206   206B        1181511SW  ALLSN 250C  250C20      03013GL                              COMPRESSOR      ERODED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            1677  CAC33790                                            (CAN) AIRCRAFT WAS IN FOR AN INSPECTION. THE COMPRESSOR CASE HALVES HAD 23 HOURS LT TO A 1750 INSPECTION. MFG REQUESTED THAT WE CARRY OUT THE INSPECTION. IT WAS FOUND THAT THE 2ND AND 3RD STAGE STATOR BLADES WERE SO UNDER CUT FROM EROSION (NEAR THE ROOT OF THE BLADES) THAT A COMPRESSOR BLADE FAILURE WAS GOING TO OCCUR. IN SOME SPOTS THE PLASTIC LINEAR WAS ERODED TO THE BARE METAL. THE AIRCRAFT DOES HAVE A INTAKE PARTICLE SEPARATOR KIT INSTALLED. ANOTHER COMPRESSOR WAS INSTALLED. (TC NR 20060818005)                                                                                                                                                                                                                         1G71 3U3  U  H2SW    E4CE                 
20061018000882006101800088NE  2006       10         18         CA060818006      120060817G291366WBL200        BOLT            NYAIRBRAKE              SKRSKYS61   S61L        8142102NE  GE    CT58  CT581401    30011NE                              HYD PUMP        BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            234   A0259                                               (CAN) THE HYDRAULIC PUMP WAS BEING REMOVED FOR MAINTENANCE PLANNING, WHEN 2 BOLT HEADS WERE FOUND TO BE SHEARED OFF, AND HELD IN PLACE BY THE LOCK WIRE. PUMP WILL BE SENT TO VENDOR FOR INVESTIGATION. PUMP WAS OPERATING NORMALLY. (TC NR 20060818006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2G72 4U4  U  1H15    1E3                  
20060913002562006091300256CE  2006       9          13         CA060821001      120060812G3242075302781       PLATE                                   CESSNA206   U206F       2073333CE  CONT  O520  IO520F      17032SO  HARTZLHCC3Y PHCC3YF1    GL  LT BRAKE SYS    CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       4000                                                           (CAN) TORQUE PLATE TOP GUIDE FOR BRAKE CALIPER CRACKED AND BROKE OFF LEAVING CALIPER ATTACHED BY BOTTOM GUIDE HOLE ONLY.   PART REPLACED WITH NEW.  (TC NR 20060821001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1H71 3O3  O  A4CE    E5CE    5  CP25EA    
20060913002572006091300257CE  2006       9          13         CA060821002      120060815G6123C1650130604     WIRE HARNESS    MCAULY      3AF32C88    CESSNA310   310Q        2074242CE  CONT  O520  TSIO520B    17040SO  MCAULY3AF32C3AF32C*     GL  PROPELLER       WRONG PART      W      O   OTHER                                                                                           W  INADEQUATE Q C                                                                CRCRUISE         1                      CA                  739222                                              (CAN) HARNESS TOO SHORT WOULD NOT ALLOW PROPELLER TO FEATHER. PILOT COULD NOT FEATHER LT OR RT PROPELLERS DURING TRAINING FLIGHT. WRONG PROPELLER DEICE WIRING HARNESSES FOUND INSTALLED AND REPLACED WITH CORRECT P/N D5855-1. (TC NR 20060821002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L72 3O3  O  3A10    E8CE    5  CP22EA    
20060913002592006091300259EA  2006       9          13         CA060821003      120060812G281021564002        FUEL CELL                               CNDAIRCL215 CL2151A10   1900320EA  PWA   PW120 PW123            NE  HAMSTD14RF  14RF19      NE  FUEL SYSTEM     LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       1361                                                           (CAN) UPON INSPECTION IT WAS DETERMINED THAT THE FUEL LEAK WAS COMING FROM THE RT FUEL CELLS. ALL 8 FUEL CELLS WERE REMOVED AND INSPECTED AND FUEL CELLS NRS 3 AND 4 AND 6 AND 8 WERE LEAKING  P/N AND S/N AND POSITION OF LEAKING CELLS. 215-64002-4 S/N 74730 NR 3 CELL 215-64002 S/N 74770 NR 4 CELL 215-64002 S/N 74586 NR 6 CELL 215-64075-1 S/N 72476 NR 8 CELL. (TC NR 20060821003)                                                                                                                                                                                                                                                                                                                                                      2H72 4R4  TRTA14EA   E20NE   6  CP11NE    
20070516001672007051600167EA  2007       5          16         CA060821004      220060808G732132447531917     FCU                                     DHAV  DHC7  DHC7102     2802708EA  PWA   PT6   PT6A50      52043EA  HAMSTD24PF  24PF305     GL  NR 1 ENGINE     FAILED          W      D   RETURN TO BLOCK                                                                                 XJ ENGINE FLAMEOUT           WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA                                                                      (CAN) AFTER INSTALLING THE FRESHLY OVERHAULED ENGINE IN THE NR 1 POSITION, THE ENGINE WAS STARTED TO PERFORM THE BETA RIGGING; THE PROPELLER WAS UNFEATHERED, THE POWER LEVEL MOVED UP TO THE FWD BETA STOP TO RECORD NUMBERS, ALL THE PARAMETERS STABILIZED.  THE NUMBERS WERE ABOUT TO BE RECORDED WHEN THE FCU. FAILED, ALL ENGINE PARAMETERS ACCELERATED.  THE POWER LEVER WAS PULLED BACK AND THE ENGINE KEPT ACCELERATING. THE T-HANDLE WAS USED TO SHUTDOWN THE ENGINE. NO ENGINE LIMITS WERE EXCEEDED. THE FCU WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THE FCU WAS FRESHLY OVERHAULED AND IT HAS BEEN RETURNED TO THE OVERHAUL FACILITY FOR REPAIR.  (TC NR 20060821004)                                                     2H74 4T4  T  A20EA   E4EA    6  CP1NE     
20061018000892006101800089CE  2006       10         18         CA060821005      120060812G7921723747          BYPASS VALVE    RAYTHN                  BEECH B300  B300        1159232CE  PWA   PT6   PT6A60A     52043NE  HARTZLHCB4M HCB4MP3     GL  OIL COOLER      FAILED          W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA       1168 1168  6176                                                (CAN) RT OIL TEMPERATURE REACHED THE REDLINE WHEN CLIMBING THROUGH 25000 FT.  POWER REDUCED AND A/C DESENDED TO 20000 FT. OIL TEMP RETURNED TO NORMAL.  ENG POWER SETTING RETURNED TO NORMAL, NO FURTHER FAULT.  NR 2 ENGINE OIL COOLER THRMOSTATIC BYPASS VALVE REPLACED IAW MM CH 79-00-00 P 9. GROUND/LEAK CHECKS PERFORMED. SYSTEM CHECKS SERVICEABLE.  (TC NR 20060821005)                                                                                                                                                                                                                                                                                                                                                                 2L72 4T4  TRTA24CE   E4EA    6  CP56GL    
20060913002602006091300260NE  2006       9          13         CA060821006      220060726G72304029T16P13P15   RETAINER        GE                                                         GE    CF34  CF343B1          NE                              FAN ROTOR       CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                  VARIOUS                 807315C                     (CAN) DURING ROUTINE SCHEDULED ENGINE MAINTENANCE, AFTER VISUAL, DIMENSIONAL, AND NON-DESTRUCTIVE INSPECTION, A HIGH NR OF FAN BLADE RETAINING PINS WERE REJECTED FOR CRACKING, DETAILS AS FOLLOWS:  ESN 807315C QTY 28 OF 28 P/N 4029T16P15 PINS CRACKED. ESN 872933 - QTY 18 OF 28 P/N 4029T16P13 PINS CRACKED. ESN 872934 - QTY 11 OF 28 P/N 4029T16P13 PINS CRACKED.  FURTHER INVESTIGATION AND REVIEW  INDICATES THAT THE REJECT RATE FOR THESE COMPONENTS MAY BE UNUSUALLY HIGH ON THE SUBJECT ENGINES.  DUE TO THE CRITICAL NATURE OF THE COMPONENT, HAVE INITIATED COMPONENT FAILURE INVESTIGATIONS.   PRODUCT SUPPORT ENGINEERING HAS REPORTED THIS CONDITION TO THE FAA, REF. FM&D REPORT CF34-3/06-02. (TC NR 20060821006)                  4  F          E15NE                
20060913002612006091300261CE  2006       9          13         CA060822001      120060805G3246                BOLT            BFGOODRICH              CESSNA650   650         2076802CE  GARRTTTPE731TFE7313C         WP                              MLG WHEEL       BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       6248       1841                                                (CAN) ON DAILY INSPECTION, FOUND (1) BOLT BROKEN ON NR 4 MAIN WHEEL ASSY. (TC NR 20060822001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  F  A9NM    E6WE                 
20061018000902006101800090EU  2006       10         18         CA060822002      120060818G3246C201950001      WHEEL                                   AIRBUS310   A310               EU  GE    CF6   CF680C2*         GL                              MLG             CRACKED         W      D   RETURN TO BLOCK                                                                                 J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      CA                                                                      (CAN) DURING THE AIRCRAFT PUSHBACK, IT WAS NOTED ON THE ECAM THAT NR 8 MAIN WHEEL WAS LOOSING PRESSURE. AFTER RETURNING TO THE GATE, IT WAS CONFIRMED USING A REGULAR TIRE PRESSURE GAUGE THAT THE PRESSURE WAS DROPPING. USING LEAK DETECTOR FLUID, IT WAS DETERMINED TO BE LEAKING FROM A CRACK BETWEEN TWO TIE BOLTS IN THE OUTER HUB SECTION. WHEEL WAS REPLACED AND ROUTED TO THE REPAIR SHOP FOR INVESTIGATION.  (TC NR  20060822002)                                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA35EU   E23EA                
20061018000912006101800091EU  2006       10         18         CA060822003      120060816G2910A29181081000    LINE                                    AIRBUS310   A310               EU  GE    CF6   CF680C2*         GL                              HYDRAULIC SYS   CHAFED          W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) DURING ROUTINE MAINTENANCE INSPECTION, FOUND NR 1 ENGINE DRIVEN PUMP OUTLET PRESSURE TUBE OF GREEN HYDRAULIC SYSTEM CHAFED BY THE AILERON TRIM INPUT CABLE AT REAR SPAR OB OF RIB 5A. HYDRAULIC TUBE REPLACED. CAMPAIGN INITIALIZED TO VERIFY THE REST OF THE FLEET AND ALL FINDING WILL BE REPORTED TO MFG FOR EVALUATION.  (TC NR 20060822003)                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA35EU   E23EA                
20060913002632006091300263NM  2006       9          13         CA060822004      120060727G7160001A716E1000010 INTAKE                                  DORNERDO32  DO328100    2996000NM                                                               NR 1 ENGINE     DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       4393                                                           (CAN) OUR AC WAS ABOUT TO DEPART WHEN DEFECT WAS SPOTTED.  DURING A NORMAL PRE-FLIGHT PILOT WALK AROUND OUR PILOT NOTICED A GAP/ ABNORMAL SPACE BETWEEN THE LOWER ENGINE INLET AND THE UPPER MATING COWL.  WE GROUNDED THE A/C TO AOG STATUS AND SENT AME`S TO RESCUE.  AME`S DISCOVERED QTY. 3 MISSING MOUNTING HARDWARE BOLTS, NUTS AND WASHERS, WHICH ARE STILL MIA.  ALSO QTY. 1 MOUNTING BOLT WAS FOUND STILL IN PLACE BUT WAS SHEARED OFF COMPLETELY AND THE APPARENT STRESS CAUSED THE ENGINE METAL MATING FLANGE TO BREAK A 1 INCH DIA. APPROX SECTION OFF AT THE FWD. OB AREA.  AME REPLACED THE LOWER INLET ASSY. WITH SAME P/N AND S/N AND ADDED THE WIDER WASHERS MINOR REPAIR IAW MM 72-20-00-300-801-A01-001.  A (SPR)  SERVICE PR2H72 4T    RTA45NM                        
20060913002642006091300264NM  2006       9          13         CA060822005      120060822G2710BACP30F9        PULLEY                                  BOEING737   737522      138449FNM  CFMINTCFM56 CFM563C1    13802EU                              RT AILERON      CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A PHASE CHECK, A GRINDING NOISE WAS HEARD WHEN THE AILERON WAS MOVED BY HAND TO CHECK FOR FREEDOM OF MOVEMENT. UPON FURTHER INVESTIGATION,THE BOLT HOLDING THE PULLEY IN PLACE WAS REMOVED AND THE BEARING FELL APART.  BEARING WAS SEVERELY CORRODED AND BUSHING FOUND TO BE GOUGED.  PULLEY AND BUSHING REPLACED.  TIMES:  36,972.52  CYCLES: 23,427 (TC NR 20060822005)                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRTA16WE   E21EU                
20061018000922006101800092CE  2006       10         18         CA060822006      120060822G5311504200285758    FRAME                                   BEECH 90    E90         1152914CE  PWA   PT6   PT6A28           EA  HARTZLHCB3T HCB3TN3     GL  BS 176          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       22986                                                          (CAN) LT SIDE OF FUSELAGE, DISCOVERED 4 LOOSE RIVETS AT FS 176.5. MAINTENANCE DEPT REMOVED INTERIOR TO INVESTIGATE DEFECT.  IT WAS DISCOVERED THAT FRAME MEMBER P/N  50-420028-57 WAS CRACKED IN SEVEN SPOTS.  MAINTENANCE DECIDED TO INVESTIGATE THE RIGHT HAND OF FUSELAGE EVEN THOUGH NO INDICATION FROM OUTSIDE OF AIRCRAFT.  ONLY THREE CRACKS WERE DISCOVERED THERE TO FRAME P/N  50-420028-58.  TOTAL CYCLES SINCE LAST DETAILED FUSELAGE INSPECTION OF THESE AREAS IN 1859.  REPETITIVE EVERY 3000 CYCLES.  NO PREVIOUS DAMAGE NOTED. (TC NR 20060822006)                                                                                                                                                                               1L72 3T4  T  3A20    E4EA    6  CP15EA    
20061018000932006101800093GL  2006       10         18         CA060822008      120060814G2820C2P2009         LINE                                    DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE  HARTZLHCB3R HCB3R304    GL  FUEL SYSTEM     CORRODED        W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) ON INSPECTION, NOTICED FUEL PIPE FROM PUMP TO SHUT-OFF VALVE (BEHIND ENGINE) STAINED GREEN, FOUND CLEARANCE BETWEEN PIPE AND RUDDER PEDAL TQ TUBE INSUFICIENT CAUSING FRETTING/DISSIMILAR CORROSION PITTING ON TUBE CAUSING FUEL LEAK (TC NR 20060822008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1H71 3R3  RRCA806    5E1     5  CP28EA    
20061018000942006101800094NM  2006       10         18         CA060823001      120060823G2710BACP30F9        PULLEY                                  BOEING737   737522      138449FNM  CFMINTCFM56 CFM563C1    13802EU                              LT AILERON      SEIZED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A PHASE CHECK THE LT AILERON CABLE PULLEY WAS FOUND TO HAVE A SEIZED BEARING AND A WORN PULLEY.  PULLEY AND BEARING REPLACED.  A FLEET CAMPAIGN WILL BE INIATED TO CHECK ALL AILERON PULLEYS FOR FREEDOM OF MOVEMENT AND BEARING CHECK.  TIMES:  36,972.52  CYCLES:  23,427 (TC NR 20060823001)                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F4  FRTA16WE   E21EU                
20061018000952006101800095GL  2006       10         18         CA060823002      320060822G6114                HUB                                     LKHEED188   188LKHEED*         WP  ALLSN 501D  501D13      03004GL  ALLSN A6441 A6441FN606  GL  PROPELLER       LEAKING         W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         KRJFLUID LOSS                PARTIAL RPM/PWR LOSS      WARNING INDICATION        CRCRUISE         1                      CA            659                                       HC2555          (CAN) RPM DROOPED TO 13,400 RPM. ENGINE SHUTDOWN AND LANDING IAW SOP. PROP OIL LEAKING OUT OF VENT HOLE IN PROPELLER HUB. (TC NR 20060823002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L74 4T4  T  4A22    E282    6  CP898     
20061213001392006121300139    2006       12         13         CA060824002      120060821G324650140251        RETAINING RING                                                                                                                          MAIN WHEEL      CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) DURING SHOP VISIT AND UPON DISASSEMBLY FOR TIRE REPLACEMENT, RETAINING RING FOR THE OUTER WHEEL HALF FOUND SPLIT AXIAL APPROXIMATELY 60 PERCENT OF ITS CIRCUMFERENCE. (TC NR 20060824002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           
20060913002682006091300268WP  2006       9          13         CA060824003      220060818G73228978017         FUEL CONTROL                            SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP  HARTZLHCB3T HCB3TN5     GL  LT ENGINE       MALFUNCTIONED   W      E   ENGINE SHUTDOWN                                                                                 XJ ENGINE FLAMEOUT           WARNING INDICATION                                  LDLANDING        1                      CA            2552                                                      (CAN) UPON LANDING, CREW APPLIED REVERSE THRUST.  BELOW 70 KIAS, THE RPM LEVER WAS SELECTED TO (LOW).  ON THE TAXIWAY, THE CREW NOTED VERY LOW ENGINE RPM, LOW OIL PRESSURE LIGHT, AND LOW EGT.  THEY DETERMINED THE ENGINE HAD FLAMED OUT AND PARTIALLY RESTARTED.  A NORMAL SHUTDOWN WAS CARRIED OUT.  A SUBSEQUENT MAINTENANCE GROUND RUN WAS ABLE TO DUPLICATE THE FAILURE, WHEN THE SPEED LEVER WAS RAPIDLY MOVED FROM HIGH TO LOW.  THE FUEL CONTROL AND FUEL PUMP WERE REPLACED WITH SERVICEABLE UNITS. (TC NR 20060824003)                                                                                                                                                                                                              2L72 4T4  TRTA8SW    E4WE    6  CP15EA    
20060913002692006091300269SW  2006       9          13         CA060824004      120060822G29102781006495      LINE                                    SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP  HARTZLHCB3T HCB3TN5     GL  HYDRAULIC SYS   LEAKING         W      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) AIRCRAFT WAS IN CRUISE, CREW NOTED HYDRAULIC LEAKAGE ON THE COCKPIT FLOOR.  CONDUCTED A NORMAL LANDING, NOSE GEAR UP LINE IN COKPIT WAS LEAKING. REPLACED LINE, ON NEXT LEG, A LINE FAILED IN THE LH GEAR WELL, CREW ACTIVATED EMERGENCY EXTENSION AND NORMAL LANDING CARRIED OUT.  THE FOLLOWING DAY ANOTHER LINE CRACKED IN THE WHEEL WELL.  MAINTENANCE SERVICED THE ACCUMULATOR AFTER THE SECOND OCCURENCE AND NOTED THE PRESSURE WAS LOW.  AFTER THE THIRD OCCURENCE, THE ACCUMULATOR WAS REPLACED AS A PRECAUTION. NO OTHER OCCURENCES THAT WEEK.  ON THE WEEKEND, MAINTENANCE PLACED THE AIRCRAFT ON JACKS, AND FOUND SMALL PRESSURE FLUCTUATIONS DUE TO A FAILED MAIN GEAR UPLOCK POWER PACK SWITCH.  THE SWITCH WAS REPLACED, THE2L72 4T4  TRTA8SW    E4WE    6  CP15EA    
20061018000962006101800096NM  2006       10         18         CA060825001      120060822G2997W44000118       WIRE                                    BOEING767   767333      1385301NM  PWA   4060  PW4060      52119NE                              HYD PUMP        CHAFED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       50063                                                          (CAN) LT ELECTRIC HYDRAULIC PUMP PRESSUE SWITCH S27 WIRING FOUND CHAFED 6 INCHES FROM CONNECTOR D56, WIRING TEMPORARILY REPAIRED IAW AMM FAULT WAS INTERMITTENT AND 4 S27 PRESSURE SWITCHS HAD BEEN REPLACED OVER THE LAST FEW MONTHS. (TC NR 20060825001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F4  FRTA1NM    E24NE                
20060913002702006091300270CE  2006       9          13         CA060825002      120060823G552007321008        HINGE                                   CESSNA185   A185F       2072821CE  CONT  O520  IO520D      17032SO  HARTZLHCC3Y HCC3YF1     GL  STABILIZER      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3522                                                           (CAN) HINGE ASSEMBLY FOR STABILIZER OB BEARING WAS FOUND CRACKED FOR BOTH ELEVATORS.  ELEVATORS REMOVED.  SEVERAL CRACKS WERE FOUND ON EACH HINGE ASSEMBLY.  HINGE ASSEMBLIES REPLACED ON STABILIZER. ALL PARTS INSTALLED USING NEW (AN) HARDWARE.  INDEPENDENT CONTROL CHECK CARRIED OUT. (TC NR 20060825002)                                                                                                                                                                                                                                                                                                                                                                                                                                  1H71 3O3  O  3A24    E5CE    5  CP25EA    
20060913002712006091300271CE  2006       9          13         CA060825003      120060513G5511053200198       SPAR                                    CESSNA172   172K        2072430CE  LYC   O320  O320E2D     41508EA  MCAULY1A175 1A175*      GL  STABILIZER      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       14693                                                          (CAN) P/N 0532001-97 SPAR REINFORCEMENT AND P/N 0532001-98 FRONT SPAR ASSEMBLY WAS REPALCED DUE TO CRACKED CENTER SECTION OF MAIN SPAR.  PARTS WERE INSTALLED USING EXISTING RIVET SIZE AND PATTERN ACCORDING TO SPECIFIED APPROVED METHODS IN MFG SRM. (TC NR 20060825003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1H71 3O3  ONT3A12    E274    5  NP857     
20060913002722006091300272CE  2006       9          13         CA060825004      120060820G7830183238001       SOLENOID                                CESSNA750   750         2076810CE                                                               THRUST REVERSER DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) FOUND THAT THE SOLINOID SHAFT HAD BEEN GROUND DOWN TO ACCOMIDATE A CLEVIS PIN THAT WAS NOT LONG ENOUGH. HALF THE MATERIAL ON THE SHAFT HAD BEEN REMOVED. THIS WAS FOUND ON INSPECTION OF THE TR SYSTEM FOR STICKY TR LEVERS. AT THIS TIME WE DO NOT THINKING THAT IT HAD ANY THING TO DO WITH THE ORIGINAL SNAG. (TC NR 20060825004)                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4J    RTT00007WI                     
20060913002742006091300274NE  2006       9          13         CA060828001      220060828G73146052T06P05      PUMP                                    CNDAIRCL601 CL6012A12   1900303EA  GE    CF34  CF343A      30015NE                              ENGINE FUEL     BROKEN          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            NRNOT REPORTED   1                      CA       5621 2673                                                      (CAN) LT MAIN AND SCAVENGE EJECTOR FAILURE (MOTIVE FLOW FAILURE). FUEL PUMP SHAFT  FOUND BROKEN. FUEL PUMP REPLACED AND AIRCRAFT RETURNED TO SERVICE.  A/C HOURS;  25194:25 CYCLES; 29896  (TC NR 20060828001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F4  FRTA21AE   E15NE                
20061018000972006101800097CE  2006       10         18         CA060828002      120060828G323025800           SELECTOR VALVE                          BEECH 90    B90         1152912CE  PWA   PT6   PT6A20      52043EA  HARTZLHCB3T HCB3TN3     GL  MLG             FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING THE SCHEDULED TASK TO LEAK CHECK THE LANDING GEAR SYSTEM (LANDING GEAR MM M-8101, ROUTINE MAINTENANCE) IT WAS NOT POSSIBLE TO BUILD PRESSURE IN THE LANDING GEAR HYDRAULIC SYSTEM WITH THE MANUAL PUMP INSTALLED. UPON INVESTIGATION IT WAS FOUND THAT FLUID WAS BEING ROUTED TO THE DOWN PORT AND THE RETURN PORT AT THE SAME TIME. ELECTRICAL POWER WAS ON THE AIRCRAFT AND THE LANDING GEAR SELECTED TO THE DOWN POSITION. THIS VALVE HAD BEEN PREVIOUSLY REMOVED FROM ANOTHER SIMILAR TYPE AIRCRAFT FOR THE SAME PROBLEM AND WAS REPAIRED. REF NR ASR-6188-011605. WHEN CYCLED USING THE AIRFRAME SYSTEM HYDRAULIC PUMP THE LANDING GEAR OPERATED CORRECTLY AND APPEARED TO NOT HAVE AN FAULTS. (TC NR 20060828002)            1L72 3T3  T  3A20    E4EA    6  CP15EA    
20061018000982006101800098CE  2006       10         18         CA060828003      120060828G323025800           SELECTOR VALVE                          BEECH 90    B90         1152912CE  PWA   PT6   PT6A20      52043EA  HARTZLHCB3T HCB3TN3     GL  MLG             MALFUNCTIONED   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) ON SCHEDULED  MAINTENANCE 1000 HRS HYD. SYSTEM 3000 PSI LEAK TEST  (LANDING GEAR MM M-8101, ROUTINE MAINTENANCE) HYD. SELECTOR FOUND LEAKING TO RETURN ON GEAR DOWN SECTION. WAS UNABLE TO BUILD UP PRESSURE TO OPERATE GEAR WITH MANUAL EXTERNAL PUMP. NEW HYD. SELECTOR INSTALLED AND IT WAS FOUND LEAKING TO RETURN ON GEAR UP SELECTION. WHEN LANDING GEAR CYCLED WITH AIRCRAFT HYD.PUMP SYSTEM OPERATES NORMALLY. SUSPECT  NOT TESTING HYD. SELECTOR VALVES BOTH OLD AND NEW VALVES OVERHAULED BY THEM. (TC NR 20060828003)                                                                                                                                                                                                          1L72 3T3  T  3A20    E4EA    6  CP15EA    
20061018000992006101800099WP  2006       10         18         CA060828004      120060827G6420                BEARING         ROBSIN                  ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              T/R PITCH LINK  WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       53                                                             (CAN) PITCH LINKS WERE FOUND TO BE CONTACTING THEIR SPACERS, CAUSING THEM TO WEAR INTO THE STAKING AROUND THE BEARING ON THE PITCH LINKS.  TAFT 53.1 HOURS.  ALL HARDWARE WAS PROPERLY INSTALLED. (TC NR 20060828004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1G71 3O3  O  H11NM   1E4                  
20061018001002006101800100WP  2006       10         18         CA060828005      120060826G6420                BEARING         ROBSIN                  ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              T/R PITCH LINK  WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       162                                                            (CAN) PITCH LINKS WERE FOUND TO BE CONTACTING THEIR SPACERS, CAUSING THEM TO WEAR INTO THE STAKING AROUND THE BEARING ON THE PITCH LINKS.  TAFT 161.6 HOURS.  ALL HARDWARE WAS PROPERLY INSTALLED.  THIS WAS THE SECOND OCCURENCE OF THIS ON OUR FLEET IN 2 DAYS.  THE MFG HAS RECENTLY CHANGED THE PART FROM B345-2 TO B345-4.  THE INSTALLATION IS THE SAME.  THIS WAS NEVER A PROBLEM WITH THE -2 PART. (TC NR 20060828005)                                                                                                                                                                                                                                                                                                                  1G71 3O3  O  H11NM   1E4                  
20061018001012006101800101SW  2006       10         18         CA060829001      120060829G2910AN937D6         FITTING                                 BELL  206   206B        1181511SW  ALLSN 250C  250C20B     03013GL                              HYD SYSTEM      CORRODED        W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) DURING INSPECTION, A LEAK WAS DISCOVERED IN THE HYDRAULIC SYSTEM PRESSURE SIDE CROSS FITTING (AN 937-D6). DISASSEMBLY REVEALED CORROSION AT MATING SURFACE OF O-RING AND CROSS. PART REPLACED WITH NEW.  O-RINGS AND RETAINING RING REPLACED. SYSTEM SERVICED WITH HYDR OIL. (TC NR 20060829001)                                                                                                                                                                                                                                                                                                                                                                                                                                          1G71 3U3  U  H2SW    E4CE                 
20060913002772006091300277EA  2006       9          13         CA060829002      220060828G8550982C9HE2        ENGINE                                  GRUMANTS2   TS2ACALFORST3951102WP  WRIGHTR1820 982C9HE2    67020EA  HAMSTD43D   43D51       NE  NR 2            OVERTEMP        W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         MJ OVER TEMP                 WARNING INDICATION                                  CLCLIMB          1                      CA            341                                                       (CAN) AIRCRAFT DEPARTED ENROUTE TO A FIRE. PILOT NOTED THE OIL TEMP ON NR 2 ENGINE WAS VERY HIGH. THE ENGINE WAS SHUTDOWN AND THE PROPELLER WAS FEATHERED. THE AIRCRAFT RETURNED AND LANDED. UPON INVESTIGATION BY MAINTENANCE STAFF, THE MAIN OIL SCREEN WAS FOUND TO BE CONTAMINATED WITH BRONZE MATERIAL. IT APPEARS THAT THE MAIN BEARING FAILED. THE ENGINE IS BEING REPLACED WITH A SERVICEABLE UNIT AND THE AIRCRAFT WILL BE RETURNED TO SERVICE. (TC NR 20060829002)                                                                                                                                                                                                                                                                    2H72 4R4  R  A25WE   E259    6  CP8879    
20061018001022006101800102EU  2006       10         18         CA060829003      120060825G3244308419030       TIRE                                    AEROSPATR42 ATR42300    8680920EU  PWA   120   PW120            NE  HAMSTD14SF  14SF5       NE  MLG             FAILED          W      C   ABORTED TAKEOFF                                                                                 O  OTHER                                                                         TOTAKEOFF        1                      CA                                                                      (CAN) ON DEPARTURE A PIECE OF TIRE WAS FOUND ON THE RUNWAY. THE AIRCRAFT CARRIED OUT A NORMAL LANDING WITHOUT FURTHER INCIDENT. MAINTENANCE REPLACED NR 1 AND 2 MAIN WHEEL ASSYS, AND THE LT MAIN GEAR DOOR DUE TO DAMAGE FROM THE DEPARTED TREAD SEGMENT (APPROX. 12 INCH X 3 INCH) BEFORE RETURNING THE AIRCRAFT TO SERVICE. (TC NR 20060829003)                                                                                                                                                                                                                                                                                                                                                                                              2H72 4T4  TRTA53EU   E20NE   6  CP7NE     
20060913002802006091300280NM  2006       9          13         CA060829004      120060805G273069403483        BEARING                                 BOEING737   737217      1384464NM  PWA   JT8   JT8D17A     52049NE                              ELEVATOR CONTROLSEIZED          W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA       64027                                                          (CAN)  AIRCRAFT ENCOUNTERED INTERMITTENT REPEAT SNAGS FOR STIFF ELEVATOR MOVEMENT.  FINAL RECTIFICATION CAME ON AUGUST 5 2006 WHEN THE REFERENCED BEARING AND RETAINER WERE REPLACED.  REFERENCED BEARING WAS FOUND SEIZED.  CURRENT MAINTENANCE PROGRAM WAS REVIEWED TOWARDS THIS FINDING.  INSP TASKS ARE CONDUCTED EVERY C CHECK.  HAS MFG HAD OTHER REPORTS OF STIFF ELEVATORS DUE TO THE REFERENCED BEARING.  2) IF SO, DOES MFG HAVE THE TOTAL TIME OF THE AIRCRAFT WITH THOSE REPORTS. (IE TO DETERMINE IF A LIFE LIMIT EXISTS)  3) MAINTENANCE C CHECK TASKS UTILIZE AMM 27-31-0.  AMM D6-12010 IS USED FOR THE AIRCRAFT INVOLVED.  AMM 27-31-0 PAGE 535 2.B CONTAINS SPRING SCALE LIMITS FOR DIFFERENT ELEVATOR DEFLECTIONS (HYDRAULICS2L72 4F4  F  A16WE   E2EA                 
20061018001032006101800103    2006       10         18         CA060829005      420060811G2565GOODRICH        SLIDE                                   BOEING767   767*               NM  GE    CF6   CF680C2B6F  30025NE                                              NO TEST         W      K   NONE                                                                                            L  NO TEST                                                                       ININSP/MAINT     1                      CA                                                                      (CAN) DURING SCHEDULED INSPECTION OF OFF-WING SLIDE COMPARTMENT DOOR LATCHES AND DISCONNECT HOUSING IAW SB 767-25A0260, BOTH OFF-WING SLIDES WERE INFLATED WITHOUT THE ASSOCIATED SLIDE COMPARTMENT DOOR BEING COMMANDED OPEN.   AS A RESULT THE COMPARTMENT DOORS, LATCHES, SLIDES AND IB FLIGHT CONTROLS WERE DAMAGED BY THE FORCE OF THE CONFINED SLIDES. ZOOM AIRLINES HAS HAD 2 PREVIOUS SIMILAR UNCOMMANDED OFF-WING SLIDE DEPLOYMENTS (JULY 29, 2005 AND SEPTEMBER 2, 2005) DURING ROUTINE MAINTENANCE.   IN BOTH PREVIOUS INCIDENTS ZOOM HAS INVESTIGATED AND TAKEN MITIGATING ACTIONS. MFG IS WELL AWARE OF THE SERVICE RELATED PROBLEMS. REF  767-FTD-25-00004, 767-FTD-25-03003,  767-FTD-25-06001.  ZOOM`S TCCA PMI HAS ASKED THAT T2L72 4F4  FRTA1NM    E13NE                
20060913002812006091300281EU  2006       9          13         CA060830001      120060828G27509787320016      WARNING SYSTEM                          PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  TE FLAPS        MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 F  FLT CONT AFFECTED                                                             CRCRUISE         1                      CA            159                                                       (CAN) 1 HR INTO CRUISE AT FL 220 PILOT EXPERIENCED INSTANTANEOUS AURAL AND VISUAL WARNINGS OF MULTIPLE SYSTEMS FAILURE. CAUTION ADVISORY PANEL DISPLAYED PUSHER INOP, FLAPS INOP, AUTO PILOT FAIL; FLAP POSITION INDICATOR JUMPED FROM 0 DEG TO 40 DEG.ALSO INDICATING RED OVERSPEED, EADI FAILED TO RAW DATA ONLY ,GEAR INDICATOR LIGHTS WENT TO THREE RED/ UNSAFE,GEAR AND FLAP WARNING TONES AUDIBLE. AFTER APPX. 20 MIN. ALL SYSTEMS SUDDENLY REVERTED TO NORMAL EXCEPT FOR THE FLAPS WHICH REQUIRED A FLAP RESET BY MAINTENANCE FLAPS THEN FUNCTION NORMALLY.PILOT COMPLETED FLIGHT AT ZERO FLAP.MAINTENACE TROUBLESHOOTING IDENTIFIED ONE FAULT CODE ON A/C COMPUTER INDICATING A POSSIBLE FLAP CONTROL WARNING UNIT  ERROR.THE FCWU WAS R1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20060913002822006091300282EA  2006       9          13         CA060830002      120060817G7810                NOZZLE                                  CNDAIRCL215 CL2156B11215       EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  RT ENG EXHAUST  DETACHED        W      E   ENGINE SHUTDOWN                                                                                 D  INFLIGHT SEPARATION                                                           TXTAXI/GRND HDL  1                      CA       4032                                                           (CAN) DURING ENGINE START-UP, AN OVERHEAT CONDITION WAS DETECTED IN THE RT ENGINE EXHAUST AREA. THE ENGINE WAS SHUTDOWN AND CAUSE OF OVERHEAT INVESTIGATED. THE INVESTIGATION REVEALED THAT A SECTION OF PRIMARY EXHAUST NOZZLE WAS COMPLETLY MISSING AND WAS EXPELLED THROUGH THE SECONDARY DUCT. THERE WERE NO OTHER DAMAGES FOUND. AN INVESTIGATION AS TO CAUSE OF THE PROBLEM WILL BE MADE BY MFG.  (TC NR 20060830002)                                                                                                                                                                                                                                                                                                                     2H72 4T4  TRTA14EA   E20NE   6  CP7NE     
20061018001332006101800133SO  2006       10         18         CA060830003      120060829G2750486597          DRIVE ASSY                              PIPER PA31  PA31350     7103110SO  LYC   O540  TIO540J2BD  41532EA  HARTZLHCE3Y HCE3YR2A    GL  RT FLAP         SHEARED         W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA                                                                      (CAN) DURING APPROACH AND FLAP EXTENSION TO 5 DEGREES CREW NOTICED AIRCRAFT ROLL TO THE RT AND OBSERVED THAT THE RT FLAP HAD NOT EXTENDED. THE LANDING WAS UNEVENTFUL. MAINTENANCE INVESTIGATION REVEALED THE RT FLAP DRIVE CABLE SPLINES AT THE MOTOR END WERE WORN AWAY. THE RT FLAP DRIVE CABLE ASSY WAS REPLACED AND OPERATION CHECKED NORMAL. (TC NR 20060830003)                                                                                                                                                                                                                                                                                                                                                                          1L72 3O3  O  A20SO   E14EA   5  CP33EA    
20060913002832006091300283NM  2006       9          13         CA060831002      120060827G32208800121         STRUT                                   DHAV  DHC8  DHC8101     2809002NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  NLG             CRACKED         W      J   DUMP FUEL                                                                                       O  OTHER                                                                         ININSP/MAINT     1                      CA       3945615435                                                     (CAN) DURING A SCHEDULED MAINTENANCE CHECK, TASK CARD 3220/01 AND 02 VISUAL INSPECTION AND LUBRICATION OF NLG ASSY, A CRACK WAS DISCOVERED IN THE NLG SHOCK STRUT HOUSING. THE NLG ASSEMBLY WAS IMMEDIATELY REPLACED.  TSN=39456.7HRS / CSN=46723CYC TSO=15435.7HRS / CSO=13147CYC TSI=799.0HRS / CSI=590CYC (TC NR 20060831002)                                                                                                                                                                                                                                                                                                                                                                                                                2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20061018001382006101800138GL  2006       10         18         CA060831004      220060828G7200                ENGINE                                  BELL  206   206L        1181522SW  ALLSN 25OC  250C20R          GL                                              POWER LOSS      W      R   AUTOROTATION                                                                                    RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) AIRCRAFT LOST POWER RESULTING IN A HARD LANDING. DATE OF OCCURRENCE, JUNE 26, 2006.  ROTORCRAFT LOST ENGINE POWER AT APPROX 400 FEET AND AUTOROTATED. AIRCRAFT IS CONSIDERED A TOTAL WRITE-OFF. TSB CURRENTLY INVESTIGATION ROOT CAUSE OF THIS EVENT.   (TC NR 20060831004)                                                                                                                                                                                                                                                                                                                                                                                                                                                               1G71 3U3  U  H2SW    E4CE                 
20060913003362006091300336NM  2006       9          13         CA060831006      120060707G6123D59901          HYDRAULIC SYSTEMHARTZL                  DORNERDO32  DO328100    2996000NM  PWA   119   PW119C           NE  HARTZLHDE6C HDE6C3B     NE  PROPELLER       FAILED          W      E   ENGINE SHUTDOWN                                                                                 O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA       4293       HL316                                               (CAN) AIRCRAFT READIED AND RT ENGINE START PARAMETERS NORMAL.  RT CONDITION LEVER ADVANCED TO MIN.  RT PROP DOES NOT UNFEATHER.  RT CONDITION LEVER RETARDED TO FEATHER.  RT CONDITION LEVER ADVANCED TO MIN.  RT PROP DOES NOT UNFEATHER.  MAINTENANCE CALLED TO SIGHT FOR  INVESTIGATION AND TROUBLESHOOTING.  PASSENGERS CHARTERED.  AIRCRAFT GROUNDED FOR 3 DAYS.  RT HYDRAULIC UNIT D-5990-1 SN S296 UNSERVICEABLE.  SN S296 TSN 4293.1.  RT HYDRAULIC UNIT D-5990-1 REPLACED WITH OVERHAULED UNIT SN S53.  HYDRAULIC UNIT SN S53 TSN 12735.5. (TC NR 20060831006)                                                                                                                                                                         2H72 4T4  TRTA45NM   E20NE   6  CP34NE    
20061018001392006101800139NM  2006       10         18         CA060901002      120060831G2920                PRESSURE SWITCH                         BOEING737   737522      138449FNM  CFMINTCFM56 CFM563C1    13802EU                              FLT CONTROL MODUUNSERVICEABLE   W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) APPROXIMATELY ONE FLIGHT HOUR ENROUTE THE (B) SYSTEM FLIGHT CONTROL MODULE LOW PRESSURE LIGHT ILLUMINATED. AIRCRAFT TURNED BACK.  (B) SYSTEM FLIGHT CONTROL MODULE REPLACED DUE TO LOW PRESSURE SWITCH UNSERVICEABLE.  TIMES- 37968:59   CYCLES: 23555 (TC NR 20060901002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F4  FRTA16WE   E21EU                
20060913003442006091300344GL  2006       9          13         CA060901003      220060823G732076715           FADEC                                   CESSNA525   525         2076601CE  WILINTFJ44  FJ44        66000GL                              RT ENGINE       FAILED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      CA       424                                                            (CAN) THE RT ENGINE FADEC CHANNEL A FAULT LIGHT ILLUMINATED. MAINTENANCE ACCESSED FADEC DATA AND DOWNLOADED FAULT CODES. FAULT CODES FORWARDED TO MFG, DURING TELEPHONE CONVERSATION WITH MFG OF AC AND ENG, IT WAS DETERMINED THAT THE FADEC HAD AN INTERNAL FAULT. AC MFG SENT A FIELD SERVICE TECHNICIAN WHO REPLACED THE FADEC AND AFTER GROUND RUNS THE SYSTEM WAS SERVICEABLE. (TC NR 20060901003)                                                                                                                                                                                                                                                                                                                                        1L72 4F4  FRTA1WI    E3GL                 
20060913003452006091300345NE  2006       9          13         CA060901004      220060823G8530399359CR        CYLINDER HEAD                           DHAV  DHC3  DHC3        2800202EA  PWA   R1340 R134059     52016NE  HAMSTD23D   23D40       NE  NR 2 CYLINDER   CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            1174                          2P103622                    (CAN) FOUND CRACK ON NR 2 CYLINDER HEAD AT EXHAUST ROCKER HOUSING WHILE CHECKING OIL LEAK AT OTHER POSITIONS. CRACK WAS NOT DETECTED AT THE LAST 100 HOUR INSPECTION. 33.5 HOURS PAST. (TC NR 20060901004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1H71 3R3  R  A815    5E2     6  CP719     
20061018001402006101800140SW  2006       10         18         CA060901005      120060818G6340                BEARING                                 AIRTRCAT802 AT802       0390305SW  PWA   PT6   PT6A67A     52043NE  HARTZLHCB5M HCB5MA3     GL  TACH GENERATOR  WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       450        86342                                               (CAN) A NOISE WAS DETECTED AND THE TACH GENERATOR WAS REMOVED AND FOUND THAT THE LOWER SHAFT BEARING WAS BADLY WORN. (TC NR 20060901005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L71 3T4  TNCA19SW   E26NE   6  CP44GL    
20060913003462006091300346WP  2006       9          13         CA060901006      220060831G73203055383         SWITCH                                  SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP                              COCKPIT         ODOR            W      C   ABORTED TAKEOFF                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      TOTAKEOFF        1                      CA            78                                                        (CAN) CREW NOTED BEFORE TAKEOFF A BURNING SMELL IN THE COCKPIT PRIOR TO TAKEOFF.  NO SYSTEM FAULTS WERE NOTED OR BREAKERS POPPED AND THE SMELL WENT AWAY, SO THE FLIGHT CONTINUED IT`S LAST LEG.  NO FAULTS NOTED IN FLIGHT.  IT WAS LATER DISCOVERED A SPEED SWITCH HAD FAILED.  THIS WAS DETERMINED TO BE THE CAUSE OF THE ELECTRICAL SMELL.  THIS UNIT HAD 77.5 HOURS TSO HOURS AND IS ONE OF A NUMBER OF FAILED SWITCHES FROM THIS VENDOR. (TC NR 20060901006)                                                                                                                                                                                                                                                                              2L72 4T4  TRTA8SW    E4WE                 
20060913003472006091300347SO  2006       9          13         CA060901007      220060822G8530T1ST712ACA      CYLINDER                                CESSNA206   U206G       2073356CE  CONT  O520  IO520F      17032SO  HARTZLHCJ3Y PHCJ3YF1    GL  CYL NR 5        SCORED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       1019 1019  69166EAB                                            (CAN) THE PILOT REPORTED AN IMPORTANT OIL LEAK TO THE AMO. AFTER INVESTIGATION, THE TECHNICIAN DISCOVERED THE SOURCE TO BE FROM  NR 5 CYLINDER BARREL O-RING. THE PISTON WAS FOUND DAMAGED, SCORED, PROBABLY CAUSED BY EXCESSIVE HEAT. PARTS REPLACED. (TC NR 20060901007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1H71 3O3  O  A4CE    E5CE    5  CP36EA    
20060913003482006091300348NM  2006       9          13         CA060901008      120060818G3231                SENSOR                                  BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  NLG DOOR        SHORTED         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB, THE LANDING GEAR STARTED TO CYCLE BY ITSELF AND SEVERAL GEAR DOOR AND GEAR UNSAFE ADVISORY LIGHTS WERE ILLUMINATED. ACCORDING QRH ALTERNATE GEAR EXTENSION PERFORMED. NORMAL LANDING PERFORMED. A/C HANDED OVER TO MAINTENANCE FOR FURTHER INVESTIGATION. INVESTIGATION FOUND THE NLGDCL SENSOR SHORTED. REPLACED NLG DOOR CLOSED SENSOR (S19) IAW FIM TASK AND PERF RIGGING OF PROXIMITY SENSOR. ALL READINGS WITHIN LIMIT. THE DAMAGE OF THE NLG DOOR CLOSED SENSOR HARNESS WAS CAUSED BY A BOLT WHICH IS INSTALLED IN THE WRONG DIRECTION. BOLT REPLACED AND DIRECTION INVERTED IAW MODSUM ISQ3200003.  BOLT INSTALLATION IS CORRECTLY SHOWN IN IPC/AMM. (TC NR 20060901008)                                             2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
20061019001112006101900111SW  2006       10         19         CA060901009      120060901G7797MS3451L10SL4P   CONNECTOR                               SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE33111U   01514WP  MCAULY4HFR344HFR34C652  NE  ENGINE          CORRODED        W      O   OTHER                                                                                           N  FALSE WARNING                                                                 LDLANDING        1                      CA                                                                      (CAN) EGT INDICATION WAS ERRATIC ON LANDING. ALL OTHER PARAMETERS WERE NORMAL. THERE WAS HEAVY PRECIPITATION PRIOR TO THE ERATIC INDICATION.  THE CONNECTOR PLUG WAS CLEANED AND RETURNED TO SERVICIBLE CONDITION.  EGT INDICATION WAS NOT ERATIC AND AIRCRAFT RETURNED TO SERVICE. (TC 20060901009)                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4T4  TRTA8SW    E4WE    6  C3PNE     
20070129003172007012900317CE  2007       1          29         CA060903001      120060624G2497                WIRE                                    CESSNA172   172M        2072418CE  LYC   O320  O320E2D     41508EA  MCAULY1C160 1C160DTM    GL  ELECTRICAL SYS  IMPROPER        W      D   RETURN TO BLOCK                                                                                 MB OVER TEMP                 SMOKE/FUMES/ODORS/SPARKS                            TXTAXI/GRND HDL  1                      CA                                                                      (CAN) OVERVOLTAGE LIGHT FOUND WIRED TO SYSTEM WITH UNAPPROVED AUTOMOTIVE WIRING. THIS WIRING DISCONNECTED, AND CAUSED A DEAD SHORT TO THE SYSTEM. (TC NR 20060903001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1H71 3O3  ONT3A12    E274    5  NP910     
20061019001122006101900112NE  2006       10         19         CA060905001      220060905G74141052947         SHAFT           CONT                    ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              MAGNETO         WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            1005  B140011ER                                           (CAN) DURING A 500 HOUR INSPECTION, THE LOWER BEARING INNER RACE WAS FOUND LOOSE ON THE SHAFT.  THE BEARING INNER RACE HAD BEEN SPINNING ON THE SHAFT CAUSING SHAFT JOURNAL TO WEAR. (TC NR 20060905001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1G71 3O3  O  H11NM   1E4                  
20061019001132006101900113SO  2006       10         19         CA060905002      120060830G3210AN626           BOLT            PIPER       1003306     PIPER PA18  PA18150     7101828SO  LYC   O320  O320A2B     41508EA  SNSNCH74D   74DM        EA  MLG             SHEARED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A ROUTINE INSPECTION OF THE AIRCRAFT, IT WAS DISCOVERED THAT THE FORWARD LT LANDING GEAR ATTACH BOLT WAS LOOSENED IN THE FUSELAGE ATTACH FITTING. CLOSER EXAMINATION FOUND THE BOLT TO BE SHEARED ABOUT HALF WAY DOWN THE SHANK OF THE BOLT. ALL FOUR LANDING GEAR ATTACHMENT BOLTS WERE REMOVED AND REPLACED WITH NEW BOLTS. THE OTHER 3 BOLTS SHOWED SIGNS OF WEAR BUT ONLY THE ONE HAD SEPARATED. (TC NR 20060905002)                                                                                                                                                                                                                                                                                                           1H71 3O3  O  1A2     E274    5  NP88614   
20060913003492006091300349CE  2006       9          13         CA060905003      120060831G212199101133        FAN BLADE                               CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              COOLING FAN     FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA                                                                      (CAN) WHEN PILOTS WERE USING FLOOD COOLING  ON THE GROUND THEY HEARED A NOISE AND HAD A VIBRATION THEY SHUT THE SYSTEM DOWN . AFTER MAINTENANCE REMOVED THE FLOOD COOLING FAN MOTOR ASSY THEY FOUND A BROKEN FAN BLADE . THEY REPLACED FLOOD COOLING FAN MOTOR ASSY P/N OFF/ON 9910113-3 S/N ON 0019  GROUND CHECKED SERVICEABLE  AND RETURNED AIRCRAFT TO SERVICE.  (TC NR 20060905003)                                                                                                                                                                                                                                                                                                                                                        1L72 4F4  F  A22CE   E1NE                 
20060914000052006091400005EU  2006       9          14         CA060905004      120060902G5554555401203       RIB                                     PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  RUDDER          BROKEN          W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             ININSP/MAINT     1                      CA                                                                      (CAN) WHILE DOING A WALK AROUND ON THE AIRCRAFT, THERE WAS LOTS OF PLAY FOUND AT THE UPPER ATTACHMENT BOLT ON THE RUDDER.  THE BOLT HAD ELONGATED THE HOLE AND DAMAGED THE NOSE RIB.  WHEN TRYING TO TAKE THE BOLT OUT, THE NUT PLATE BROKE AWAY AND A PIECE OF THE NOSE RIB THAT IT WAS RIVETED TO WAS ALREADY CRACKED FROM SO MUCH PLAY IN THE UPPER ATTACHMENT THAT IT WAS WHAT ACTUALLY BROKE AWAY WITH THE NUT PLATE.  THE UPPER BEARING WAS ALSO DAMAGED.  THE BOLT HEAD HAD TO BE CUT OFF TO GET BOLT OUT. THE RUDDER WAS REMOVED AND ANOTHER INSTALLED TO MAKE THE AIRCRAFT AIRWORTHY AGAIN.  THE DAMAGED RUDDER IS NOW AWAITING PARTS TO FACILITATE A REPAIR. (TC NR 20060905004)                                                      1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20060914000062006091400006EU  2006       9          14         CA060905005      120060902G53405531012326      BRACKET                                 PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  HYD ACTUATIOR   CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) WHILE DOING A WALKAROUND ON THE AIRCRAFT THERE WAS A CRACK FOUND ON THE UPPER ATTACHMENT BRACKET IN THE NOSE GEAR BAY THAT THE NOSE GEAR HYDRAULIC ACTUATOR ATTACHES TO.  BRACKET REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20060905005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20060914000072006091400007NE  2006       9          14         CA060905006      320060819G61127849141         BULKHEAD        HAMSTD                  DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  PROPELLER       DAMAGED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                  880512                                              (CAN) THE FLIGHT CREW SNAGGED THE PORT PROP DEICE AS U/S NO LIGHTS OR INDICATION ON AC LOAD GAUGE.  UPON FURTHER INVESTIGATION, MAINTENANCE FOUND THAT ALL 3 OF THE PROP DEICE BRUSH BLOCK SLIP RINGS HAD COME OFF OF THE PROPELLER BULKHEAD AND WERE WRAPPED AROUND THE PROPELLER SHAFT. THE SURROUNDING AREA OF THE ENGINE COMPARTMENT WAS INSPECTED FOR FURTHER DAMAGE, WITH NO OTHER DAMAGE FOUND. THE PROPELLER BULKHEAD AND DEICE BRUSH BLOCK WERE REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THE BULKHEAD HAS BEEN SENT OUT FOR REPAIR AND A STRIP REPORT. (TC NR 20060905006)                                                                                                                                                       2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20060914000082006091400008SW  2006       9          14         CA060905007      120060831G2497                WIRE                                    SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP  ROTOL R321  R321482F8   GL  BATTERY/CHARGER DAMAGED         W      O   OTHER                                                                                           J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) AIRCRAFT HAD EXPERIENCED PROBLEMS WITH BATTERY DISCONNECTING INTERMITTENTLY.  FIRST TIME WAS CIRCUIT BREAKER POPPED. NEXT TIME FOUND CORROSION ON BATTERY RELAY, REPLACED RELAY.  THIS IS A COMMON DEFECT WITH THESE TYPE OF RELAYS.  THIRD INSTANCE WAS ON NEXT LEG AFTER BATTERY RELAY WAS REPLACED.  CREW EXPERIENCED A BATTERY FAULTY ENUNCIATOR AND BOTH DISCONNECT LIGHTS INDICATED.  ONCE ON THE GROUND, THEY WERE UNABLE TO GET EITHER BATTERY ON LINE.  MAINTENANCE DISCOVERED THE 4 GAUGE FEEDER WIRES FROM THE RAH BATTERY TO THE SERIES-PARALLEL RELAY CHAFED INSIDE THE WING.  THE WIRES WERE PROTECTED WITH FIRE SLEEVE AND HAD CHAFED THROUGH.  THERE WAS ASSOCIATED DAMAGE TO THE BLEED AIR LINE THAT THE WIRES RUBBED AGA2L72 4T4  TRTA8SW    E4WE    6  CP61GL    
20060914000092006091400009EA  2006       9          14         CA060905008      220060729G7230                BLADES                                  DHAV  DHC6  DHC6        2802606EA  PWA   PT6   PT6A27      52043EA                              COMPRESSOR      DAMAGED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                          20529                       (CAN) PROBLEMS WERE REPORTED WITH THE ENGINE SHORTLY AFTER TAKE-OFF.  THE AIRCRAFT SUBSEQUENTLY CRASHED.  PRELIMINARY INVESTIGATION EVIDENSED COMPRESSOR BLADE DISTRESS.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20060905008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H72 3T4  TRTA9EA    E4EA                 
20060914000292006091400029NE  2006       9          14         CA060905009      220060727G7261                ENGINE                                  AEROSPATR42 ATR42*      8680900EU  PWA   PW121 PW121       52124NE                                              LEAKING         W      A   UNSCHED LANDING                                                                                 KB FLUID LOSS                SMOKE/FUMES/ODORS/SPARKS                            CLCLIMB          1                      CA                                          121400                      (CAN) DURING CLIMB SMOKE AND ODORS BECAME EVIDENT IN THE CABIN.  ENGINE BLEEDS WERE CLOSED AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED OIL LEAKAGE AT THE ENGINE INLET AND EXTERNALS.  MFG WILL MONITOR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20060905009)                                                                                                                                                                                                                                                                                                                                                                                                           2H72 4T4  TRTA53EU   E20NE                
20060914000372006091400037NE  2006       9          14         CA060905010      220060731G7250                BEARING                                 GULSTM200   200         4500308NM  PWA   306   PW306B           NE                              TURBINE SECTION FRACTURED       W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY AN INCREEASE IN INTER-TURBINE TEMPERATURE AND VIBRATIONS AND A CHIP DETECTOR INDICATION.  THE ENGINE WAS SHUTDOWN IN FLIGHT AND AN UNSCHEDULED LANDING CARRIED OUT.  SUBSEQUENT INSPECTION REVEALED DAMAGE TO THE LOW PRESSURE TURBINE NR4 BEARING. (TC NR 20060905010)                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F4  FRTA53NM   E35NE                
20061019001142006101900114NE  2006       10         19         CA060905011      220060731G7200                ENGINE                                  AEROSPATR72 ATR72              EU  PWA   PW121 PW121       52124NE                                              FAILED          W      A   UNSCHED LANDING                                                                                 ERJVIBRATION/BUFFET          PARTIAL RPM/PWR LOSS      WARNING INDICATION        CLCLIMB          1                      CA                                          120363                      (CAN) DURING CLIMB THE ENGINE EMITTED A LOUD NOISE.  THE ENGINE WAS SHUT DOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED METAL DEBRIS IN THE EXHAUST AND SEIZURE OF THE PROPELLER.  MFG WILL MONITOR INVESTIGATION OF THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060905011)                                                                                                                                                                                                                                                                                                                                                                                              2H72 4T4  TRT        E20NE                
20061019001152006101900115EA  2006       10         19         CA060905012      220060730G7200                ENGINE                                                                     PWA   PT6   PT6A45R     52043EA                                              FLAMED OUT      W      O   OTHER                                                                                           XJ ENGINE FLAMEOUT           WARNING INDICATION                                  CRCRUISE         1                      CA                                          84317                       (CAN) THE ENGINE FLAMED OUT IN CRUISE.  A SUBSEQUENT IN-FLIGHT RELIGHT ATTEMPT WAS UNSUCCESSFUL. INVESTIGATION REVEALED DAMAGE TO THE COMPRESSOR AND POWER TURBINE BLADES.  MFG WILL MONITOR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20060905012)                                                                                                                                                                                                                                                                                                                                                                                                                                                                  4  T          E4EA                 
20061019001162006101900116NE  2006       10         19         CA060905013      220060729G7321                FUEL CONTROL                            CESSNA500   550         2076604CE  PWA   530   PW530A           NE                              ENGINE          FAILED          W      O   OTHER                                                                                           XJ ENGINE FLAMEOUT           WARNING INDICATION                                  DEDESCENT        1                      CA                                                                      (CAN) THE ENGINE FLAMED OUT DURING DESCENT.  SUBSEQUENT INSPECTION REVEALED METAL PARTICLES IN THE FUEL SYSTEM DOWNSTREAM OF THE FUEL CONTROL UNIT. THE FUEL SYSTEM COMPONENTS WERE REPLACED. MFG WILL MONITOR INVESTIGATION OF THE FCU AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20060905013)                                                                                                                                                                                                                                                                                                                                                                                                                                           1L72 4F4  F  A22CE   E00053EN             
20061019001172006101900117NE  2006       10         19         CA060905014      220060804G7200                ENGINE                                  PILATSPC12  PC12        7090550EU  PWA   PT6   PT6A67B     52043NE                                              SMOKE           W      G   O2 MASK DEPLOYED                                                                                B  SMOKE/FUMES/ODORS/SPARKS                                                      NRNOT REPORTED   1                      CA                                                                      (CAN) THE ENGINE WAS REPORTED TO HAVE CAUSED SMOKE IN THE CABIN AIR, REQUIRING THE DEPLOYMENT OF OXYGEN MASKS.  MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED (TC NR 20060905014)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L71 3T4  TRTA78EU   E26NE                
20061019001182006101900118EU  2006       10         19         CA060905015      120060618G7500311221801       SWITCH                                  AEROSPATR72 ATR72              EU  PWA   PW120 PW124B           NE                              P2 AIR          FAILED          W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      APAPPROACH       1                      CA                                                                      (CAN) DURING APPROACH, SMOKE WAS REPORTED IN THE CABIN AIR AND ENGINE CABIN BLEED WAS SELECTED OFF.  SUBSEQUENT INSPECTION REVEALED DAMAGED P2.5 AIR SWITCHING VALVE COMPONENTS ON BOTH ENGINES (124335 AND 124297). (TC NR 20060905015)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2H72 4T4  TRT        E2ONE                
20060914000382006091400038EA  2006       9          14         CA060906001      120060811G5610NP139322001     WINDSHIELD                              CNDAIRCL600 CL6002C10   1390015EA  GE    CF34  CF348C1          NE                              COCKPIT         FAILED          W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         DEDESCENT        1                      CA                                                                      (CAN) CREW NOTED DURING DESCENT CAPT LT SIDE WINDOW SHATTERED THE MIDDLE PANE AND NO PRESSURE PROBLEMS. THEY LANDED WITH NO PROBLEMS. (TC NR 20060906001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F4  FRTA21EA   EOOO63EN             
20060914000392006091400039EA  2006       9          14         CA060906002      120060817G5610NP1393226       WINDOW                                  CNDAIRCL600 CL6002C10   1390015EA  GE    CF34  CF348C1          NE                              COCKPIT         FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA       9833                                                           (CAN) RT SIDE WINDOW CRACK. RT SIDE WINDOW IAW AMM CHANGED, WINDOW HEAT TEST PERF. OK.PLEASE PERFORM CABIN PRESS TEST. CABIN PRESS TEST PERF. FOUND OK. (TC NR 20060906002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA21EA   EOOO63EN             
20060914000402006091400040EA  2006       9          14         CA060906003      120060822G5610NP15932211      WINDOW                                  CNDAIRCL600 CL6002C10   1390015EA  GE    CF34  CF348C1          NE                              COCKPIT         FAILED          W      D   RETURN TO BLOCK                                                                                 O  OTHER                                                                         CRCRUISE         1                      CA       3947                                                           (CAN) LT SIDE WINDOW SHATTERED IN FLIGHT AT FL300 CABIN DIFF 8.2, REDUCE PRESS TO 6.2. QRH INITIATED. MAINTENANCE REPLACED THE LT SIDE WINDOW. (TC NR 20060906003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F4  FRTA21EA   EOOO63EN             
20060914000412006091400041EA  2006       9          14         CA060906004      120060826G5610NP1393225       WINDOW                                  CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF348C1          NE                              COCKPIT         CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA       10052                                                          (CAN) LT WINDOW CRACKED. LT SIDE WINDOW IAW AMM 56-12-01 REPLACED. (TC NR 20060906004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA21EA   EOOO63EN             
20060914000422006091400042EA  2006       9          14         CA060906005      120060828G2150GG67065009      ACM                                     CNDAIRCL600 CL6002C10   1390015EA  GE    CF34  CF348C1          NE                              LEFT            SMOKE           W      D   RETURN TO BLOCK                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      TXTAXI/GRND HDL  1                      CA       9784                                                           (CAN) DISC- BURN/SMOKE ODOR IN COCKPIT, SMOKE ODOR TEMPORARY LT PACK AUTO FAIL ISSUED MEL 2112. C/A - RAI LT ACM IAW CRJ 700 AMM 21-51-08 OPS CK, LEAK CHECK GOOD MEL RESTORED. (TC NR 20060906005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F4  FRTA21EA   EOOO63EN             
20061019001192006101900119EU  2006       10         19         CA060906006      120060903G3150                WARNING SYSTEM                          AIRBUS310   A310304     3930339EU  GE    CF6   CF680C2A5        NE                                              MULTIPLE IND    W      C   ABORTED TAKEOFF                                                                                 GJ MULTIPLE FAILURE          WARNING INDICATION                                  TOTAKEOFF        1                      CA                                                                      (CAN) AT 50 KNOTS, FLIGHT CREW REJECTED TAKE OFF DUE TO NAV ADC, GPS DISAGREE WARNING. DURING TAXI TO THE GATE, FAULT CLEARED IT`S SELF. FMS WAS RESET IAW MM, GPS, IRS AND FM POSITIONAL FOUND MATCHING. AUTO FLIGHT SYSTEMS TESTED AND FOUND SERVICEABLE. AIRCRAFT WAS DISPATCHED WITH NO FURTHER PROBLEM.  (TC NR 20060906006)                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F4  FRTA35EU   E13NE                
20060914000432006091400043GL  2006       9          14         CA060906007      220060905G725023076977        TURBINE BLADES                          EMB   145   EMB145LR    3260212SO  ALLSN AE300 AE3007A          GL                              ENGINE          MISINSTALLED    W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA                                          A710015                     (CAN) ENGINE HAS BEEN ASSEMBLED WITH THE WRONG HP1 TURBINE BLADES PN CONFIGURATION.  THE HP1 TURBINE BLADES INSTALLED ARE POST SB 72-260 ENGINES; NEW HIGH PRESSURE TURBINE UPGRADE (BLOCK111) WHEN THE ENGINE IS PRE SB 72-260 CONFIGURATION.  THE OEM (INDIANAPOLIS) HAS BEEN NOTIFIED TO DETERMINED IF THE BLADES COULD REMAIN IN THE ENGINE IN SERVICE. (TC NR 20060906007)                                                                                                                                                                                                                                                                                                                                                                 2L72 4T4  FRTT00011ATTE6CH                
20060914000442006091400044GL  2006       9          14         CA060906008      220060905G725023076977        TURBINE BLADES                          EMB   145   EMB145      3260210SO  ALLSN AE300 AE3007A          GL                                              MISINSTALLED    W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA                                          A71843                      (CAN) ENGINE HAS BEEN ASSEMBLED WITH THE WRONG HP1 TURBINE BLADES PN CONFIGURATION.  THE HP1 TURBINE BLADES INSTALLED ARE POST SB 72-260 ENGINES; NEW HIGH PRESSURE TURBINE UPGRADE (BLOCK111) WHEN THE ENGINE IS PRE SB 72-260 CONFIGURATION.  THE OEM (INDIANAPOLIS) HAS BEEN NOTIFIED TO DETERMINED IF THE BLADES COULD REMAIN IN THE ENGINE IN SERVICE. (TC NR 20060906008)                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTT00011ATTE6CH                
20060914000452006091400045GL  2006       9          14         CA060906009      220060905G725023079436        TURBINE BLADES                          EMB   135   EMB135ER    3260203SO  ALLSN AE300 AE3007A          GL                              ENGINE          MISINSTALLED    W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA                                          A71332                      (CAN) ENGINE HAS BEEN ASSEMBLED WITH THE WRONG HP1 TURBINE BLADES PART NUMBER CONFIGURATION.  THE HP1 TURBINE BLADES INSTALLED ARE POST SB 72-260 ENGINES; NEW HIGH PRESSURE TURBINE UPGRADE (BLOCK111) WHEN THE ENGINE IS PRE SB 72-260 CONFIGURATION.  THE OEM (INDIANAPOLIS) HAS BEEN NOTIFIED TO DETERMINED IF THE BLADES COULD REMAIN IN THE ENGINE IN SERVICE. (TC NR  20060906009)                                                                                                                                                                                                                                                                                                                                                       2L72 4F4  FRTT00011ATTE6CH                
20061019001202006101900120EU  2006       10         19         CA060906011      120060906G5280                SKIN                                    BRAERODH125 HS125700A   4230170EU  GARRTTTFE731TFE7313R    01518WP                              MLG DOOR        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       9668                                                           (CAN) DURING REMOVAL FOR ACCESS, A GENERAL VISUAL INSPECTION OF THE RT MAIN GEAR DOOR REVEALED A LARGE CRACK IN THE INNER SKIN PANEL AS WELL AS SEVERAL PULLED RIVETS ADJACENT TO THE GEAR DOOR JACK ATTACH BRACKET.  SB 32-192-2845 (TO PREVENT CRACKING OF THE BRACKET ITSELF) HAD BEEN PREVIOUSLY EMBODIED AT 4608.6 HOURS TSN AND 3015 CYCLES.  THE CRACK HAD PROPAGATED TO 6 INCHES IN LENGTH ALONG THE FORWARD IB EDGE OF THE STRENGTHENED (POST MOD) BRACKET IN THE STRUCTURE THE BRACKET IS ATTACHED TO: THE INNER DOOR PAN.  A SOFT (TC NR 20060906011)                                                                                                                                                                                2L72 4F4  F  A3EU    E6WE                 
20061019001222006101900122NE  2006       10         19         CA060906012      220060904G72302292152810      COMPRESSOR                              SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1        NE                              ENGINE          FOD             W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2236 2236                          9922                        (CAN) DURING ROUTINE INSPECTION IT WAS NOTED THAT THE AXIAL COMPRESSOR WHEEL HAD SUFFERED FOD, WHICH WAS BEYOND LIMITS. THERE WAS NO EVIDENCE THAT THE INTAKE COWL HAD LOST ANY HARDWARE WHICH MAY HAVE CAUSED THIS. NOR WAS THERE ANY RESIDUAL PARTICLES/OBJECTS FOUND IN THE INTAKE SCOOP. THE AXIAL COMPRESSOR WHEEL WAS CHANGED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060906012)                                                                                                                                                                                                                                                                                                                                               1G71 3U3  U  H9EU    E19EU                
20061019001292006101900129NE  2006       10         19         CA060906013      220060907G7200                ENGINE                                  BEECH MU300 400A        1155402CE  PWA   JT15  JT15D5      52112NE                                              FLAMED OUT      W      G   O2 MASK DEPLOYED                                                                                XJ ENGINE FLAMEOUT           WARNING INDICATION                                  CRCRUISE         1                      CA                                          JA0626                      (CAN) THE AIRCRAFT ENTERED RAIN AND TURBULENCE AT 40K FEET AND THE ENGINE FLAMED OUT.  ENGINE ANTI-ICE AND CONTINUOUS IGNITION HAD NOT BEEN SELECTED.  THE ENGINE WAS SUCCESSFULLY RE-STARTED AT 28K FEET.  MFG WILL MONITOR THE INVESTIGATION OF THIS EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060906013)                                                                                                                                                                                                                                                                                                                                                                                                                2H72 4F4  FRTA16SW   E25EA                
20061019001302006101900130SW  2006       10         19         CA060906014      120060906G2897MS3456W14S5S    CONNECTOR       BELL                    BELL  412   412EP       1182205SW  PWA   PT6T  PT6T3       52045EA                              FUEL VALVE      SHORTED         W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      CA                  T71706                                              (CAN) FLASHING LIGHT OF ENGINE FUEL VALVE NR 2 ON STARTING PROCEDURE. CONNECTOR 1B14P1 SHORTED TOGETHER BETWEEN PINS A AND B AND WATER CONTAMINATION FOUND INSIDE BACK SHELL. INTERNAL LEAKAGE MEASURED ON THE CONNECTOR BETWEEN PINS A AND B CAUSING ON-OFF SIMULTANEOUS COMMANDS AND DAMAGES TO THE VALVE (205-060-612-003). CONNECTOR AND VALVE REPLACED AND A/C RETURNED TO SERVICE.  A/C HOURS 1754:16 A/C CYCLES  1904  (TC NR 20060906014)                                                                                                                                                                                                                                                                                               1G72 4U4  U  H4SW    E22EA                
20061019001312006101900131NE  2006       10         19         CA060906015      220060815G7200                ENGINE                                  CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE                                              FLAMED OUT      W      A   UNSCHED LANDING                                                                                 XJ ENGINE FLAMEOUT           WARNING INDICATION                                  CRCRUISE         1                      CA                                          19374                       (CAN) THE ENGINE WAS REPORTED TO EMIT A LOUD BANG IN FLIGHT FOLLOWED BY A FLAMEOUT.  A DEAD-STICK LANDING WAS ACCOMPLISHED.  SUBSEQUENT INSPECTION REVEALED DEBRIS IN THE ENGINE OIL FILTER AND SEIZURE OF THE COMPRESSOR.  MFG WILL INVESTIGATE THE EVENT AND ADVSE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060906015)                                                                                                                                                                                                                                                                                                                                                                                                                        1H71 3T3  T  A37CE   E4EA                 
20061019001322006101900132EA  2006       10         19         CA060906016      220060818G73143031709         PUMP                                                                       PWA   PT6   PT6A27      52043EA                              FUEL SYSTEM     FAILED          W      C   ABORTED TAKEOFF                                                                                 XJ ENGINE FLAMEOUT           WARNING INDICATION                                  TOTAKEOFF        1                      CA       5439                                                           (CAN) THE ENGINE FLAMED OUT DURING TAKE-OFF ROLL AND THE TAKE-OFF WAS ABORTED. METAL DEBRIS WAS FOUND IN THE FUEL PUMP OUTLET FILTER. (TC NR 20060906016)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              4  T          E4EA                 
20061019001332006101900133CE  2006       10         19         CA060906017      120060818G7712                ENGINE                                  BEECH 200   B200        1152922CE  PWA   PT6   PT642A           NE                                              MALFUNCTIONED   W      E   ENGINE SHUTDOWN                                                                                 RF PARTIAL RPM/PWR LOSS      FLT CONT AFFECTED                                   APAPPROACH       1                      CA                                          PJ0711                      (CAN) ENGINE TORQUE WAS SEEN TO FLUCTUATE ON APPROACH AND THE ENGINE WOULD NOT RESPOND TO THROTTLE INPUT.  THE ENGINE WAS SHUTDOWN IN FLIGHT. MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060906017)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L72 4T4  T  A24CE   E4EA                 
20061019001342006101900134NE  2006       10         19         CA060906018      220060717G7250                ENGINE                                  CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE                                              DAMAGED         W      E   ENGINE SHUTDOWN                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      CA                                          PC0472                      (CAN) DURING CLIMB THE ENGINE EMITTED A LOUD BANG ACCOMPANIED BY A LOSS IN POWER AND AN AGB CHIP DETECTOR INDICATION.  THE ENGINE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED DEBRIS IN THE ACCESSORY AND REDUCTION GEARBOXES AND POWER TURBINE ROTOR DAMAGE.  MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20060906018)                                                                                                                                                                                                                                                                                                                                                                   1H71 3T3  T  A37CE   E4EA                 
20061019001352006101900135NM  2006       10         19         CA060906019      120060703G7931                SEAL                                    DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  ENG OIL PUMP    LEAKING         W      E   ENGINE SHUTDOWN                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  NRNOT REPORTED   1                      CA                                                                      (CAN) ENGINE OIL PRESSURE WAS REPORTED TO FLUCTUATE IN FLIGHT AND THE ENGINE WAS SHUT DOWN. SUBSEQUENT INSPECTION REVEALED A LEAKING HYDRAULIC PUMP PAD OIL SEAL. (TC NR 20060906019)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20061023000752006102300075NE  2006       10         23         CA060906020      220060826G7230                FAN BLADE                                                                  PWA   306   PW306B           NE                              COMPRESSOR      DAMAGED         W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      CA                                          CD0046                      (CAN) DURING CLIMB THE ENGINE WAS REPORTED TO EMIT A LOUD NOISE ACCOMPANIED BY AN UNCOMMANDED REDUCTION IN POWER.  THE ENGINE WAS SHUT DOWN, AN EMERGENCY DECLARED AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED METAL DEBRIS IN THE ENGINE EXHAUST AND A HEAVY FAN BLADE RUB.  PWC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                           4  F          E35NE                
20061019001362006101900136NE  2006       10         19         CA060906021      220060828G7321305964401       FUEL CONTROL                            BEECH 200   200BEECH    1152920CE  PWA   PT6   PT642A           NE                              PNEUMATIC       CONTAMINATED    W      E   ENGINE SHUTDOWN                                                                                 F  FLT CONT AFFECTED                                                             CLCLIMB          1                      CA                                                                      (CAN) ENGINE TORQUE WAS SEEN TO FLUCTUATE DURING CLIMB.  DURING DESCENT ENGINE TORQUE INCREASE UNCOMMANDED AND THE ENGINE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INVESTIGATION REVEALED CONTAMINATION OF THE PNEUMATIC SECTION OF THE FUEL CONTROL UNIT. (TC NR 20060906021)                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 4T4  T  A24CE   E4EA                 
20061019001372006101900137NE  2006       10         19         CA060906022      220060907G7261                SEAL                                    DORNERDO32  DO328100    2996000NM  PWA   119   PW119C           NE                              ALTERNATOR DRIVELEAKING         W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         KJ FLUID LOSS                WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) FOLLOWING TAKEOFF ENGINE OIL PRESSURE WAS SEEN TO FLUCTUATE AND DECAY TO ZERO.  THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED A LEAKING ALTERNATOR DRIVE SEAL. (TC NR 20060906022)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2H72 4T4  TRTA45NM   E20NE                
20061019001382006101900138    2006       10         19         CA060906023      120060824G7931                TRANSDUCER                                                                 PWA   PW120 PW127            NE                              OIL PRESSURE    DIRTY           W      E   ENGINE SHUTDOWN                                                                                 N  FALSE WARNING                                                                 DEDESCENT        1                      CA                                                                      (CAN) DURING DESCENT THE ENGINE LOW OIL PRESSURE WARNING ANNUNCIATED.  THE ENGINE WAS SHUTDOWN IN FLIGHT.  THE ENGINE OIL PRESSURE TRANSDUCER WAS SUBSEQUENTLY REMOVED, CLEANED AND RE-INSTALLED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20060906023)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             4  T          E20NE                
20061019001392006101900139CE  2006       10         19         CA060906024      120060829G27501005240731      MOTOR                                   BEECH 100   A100        1152915CE  PWA   PT6   PT6A28           EA  HARTZLHCD4N3HCD4N3A     GL  TE FLAP         FAILED          W      A   UNSCHED LANDING                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      NRNOT REPORTED   1                      CA            3851                                                      (CAN) SHORTLY AFTER TAKEOFF, AT APPROXIMATELY 1000 FEET ALTITUDE A LIGHT SMOKE APPEARED IN THE CABIN ACCOMPANIED WITH A BURNING SMELL. THE AIRCRAFT IMMEDIATELY RETURNED TO THE DEPARTURE AIRPORT. FURTHER INVESTIGATION BY MAINTENANCE REVEALED THAT THE FLAP MOTOR WAS BURNED OUT AND WAS THE CAUSE OF THE SMOKE AND BURNING SMELL. THE FLAP MOTOR AND GEARBOX WERE REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20060906024)                                                                                                                                                                                                                                                                                                        1L72 3T4  T  A14CE   E4EA    5  CSTC      
20061019001402006101900140EU  2006       10         19         CA060906025      120060802G6123311809101       AUTOFEATHER SYS                         AEROSPATR72 ATR72              EU  PWA   PW120 PW127            NE                              PROPELLER       FAULTY          W      E   ENGINE SHUTDOWN                                                                                 F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA       4265                                                           (CAN) ON APPROACH THE PROPELLER FEATHERED UNCOMMANDED AND THE ENGINE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INVESTIGATION REVEALED A FAULTY AUTO FEATHER UNIT. (TC NR 20060906025)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2H72 4T4  TRT        E20NE                
20070504001272007050400127CE  2007       5          4          CA060906026      120060831G5610991438012       WINDSHIELD                              CESSNA750   750         2076810CE  ALLSN AE3007AE3007C          GL                              COCKPIT         FAILED          W      B   EMER. DESCENT                                                                                   O  OTHER                                                                         CRCRUISE         1                      CA       542                                                            (CAN) IN CRUISE AT 41000 FEET A SOUND LIKE A SHOTGUN WAS HEARD AND THE RT WINDSHIELD OUTER PANE SHATTERED.  AFTER AN UNSCHEDULED LANDING AND INSPECTION BY AN AME IT WAS DETERMINED TO BE EITHER A LIGHTNING STRIKE OR A SHORT OF THE HEATING ELEMENT.  THE WINDOW WAS THEN REPLACED AND A LIGHTNING STRIKE INSPECTION WAS COMPLIED WITH. THE AIRCRAFT WAS THEN RETURNED TO SERVICE. (TC NR 20060906026)                                                                                                                                                                                                                                                                                                                                        2L72 4J4  FRTT00007WITE6CH                
20061019001412006101900141CE  2006       10         19         CA060907002      120060901G32404500SA1         VALVE                                   BEECH 100   100BEECH    1152916CE  PWA   PT6   PT6A28           EA  HARTZLHCD4N3HCD4N3A     GL  PARK BRAKE      FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         LDLANDING        1                      CA       10221                                                          (CAN) RT BRAKE WOULD NOT RELEASE AFTER TOUCHDOWN, AIRCRAFT STOPPED ON RUNWAY, BRAKE PRESSURE HAD TO BE RELEASED BEFORE AIRCRAFT REMOVED FROM RUNWAY. RT BRAKE MASTER CYLINDER REPLACED WITH USED SERVICEABLE UNIT. OPERATION CHECK CARRIED OUT OKAY. DURING TAKEOFF THE CREW FELT A LUNGE FORWARD AFTER ROTATION. THEY FELT THE BRAKE WAS STILL DRAGGING SO THEY DECIDED TO DIVERT FROM  AIRPORT . REQUESTED ERS STANDBY, ANTICIPATING POSSIBLE DIRECTIONAL CONTROL PROBLEMS AFTER TOUCHDOWN. AIRCRAFT LANDED WITHOUT INCIDENT. FURTHER INVESTIGATION REVEALED PROBLEMS WITH THE RT PARK BRAKE VALVE P/N 4500SA1. WHEN THE RT BRAKE PEDAL WAS DEPRESSED, THE PARK BRAKE VALVE HELD PRESSURE, AND WOULD NOT RELEASE THE RT BRAKE. THE PARK BRAKE 1L72 3T4  T  A14CE   E4EA    5  CSTC      
20061019001422006101900142EA  2006       10         19         CA060907003      220060905G7421                SPARK PLUG                              PIPER PA31  PA31350     7103110SO  LYC   O540  TIO540J2BD  41532EA  HARTZLHCE3Y HCE3YR2A    GL  LT ENGINE       FOULED          W      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      CA                                          L411961A                    (CAN) AIRCRAFT (CARGO FLIGHT, NO PASSENGERS, 2 CREW ON BOARD) RETURNED AFTER TAKEOFF WITH REPORT OF LT ENGINE RUNNING VERY ROUGH AND PARTIAL POWER LOSS AS INDICATED BY SLIGHT YAW OF THE AIRCRAFT AND LT ENGINE RPM FLUCTUATION OF APPROX. 200 RPM. MAINTENANCE INVESTIGATION REVEALED NR3 CYLINDER SPARK PLUGS FOULED; REPLACED WITH NEW FINE-WIRE TYPE PLUGS AND GROUND RUN CHECKED SERVICEABLE. SNAG REOCCURRED NEXT FLIGHT AND AIRCRAFT TAKEN OUT OF SERVICE FOR MAINTENANCE. ALL LT ENGINE FUEL INJECTOR NOZZLES CLEANED, ALL FUEL INJECTOR LINES CLEANED AND GROUND RUN CHECKED SERVICEABLE. AIRCRAFT TEST FLIGHT AND SUBSEQUENT FLIGHTS WITH LH ENGINE OPERATION NOW NORMAL. (TC NR 20060907003)                                        1L72 3O3  O  A20SO   E14EA   5  CP33EA    
20061019001432006101900143SW  2006       10         19         CA060907004      120060629G7170                O-RING                                  BELL  212   212         1181420SW  PWA   PT6T  PT6T3B      52045NE                              DRAIN VALVE     UNSERVICEABLE   W      E   ENGINE SHUTDOWN                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA                  NA                                                  (CAN) STARTED NR 2 ENGINE FIRST.  SECOND START OF THE DAY.  STARTED NR 1 AND BROUGHT IT UP TO IDLE.  THE AME CAME RUNNING TO THE COCKPIT AND GAVE THE SIGNAL TO SHUTDOWN THE ENGINE.  ENGINE WAS SHUT DOWN AND BOOST PUMP TURNED OFF.  HE SAID FUEL WAS STILL LEAKING FROM THE DRAIN AND TO TURN NR 2 BOOST PUMP OFF.   NR 2 BOOST PUMP WAS TURNED OFF.  SHORTLY THERE AFTER NR 2 ENGINE FLAMED OUT AND QUIT.  ALL BOOST PUMPS AND FUEL VALVES CLOSED.  ENGINES SECURED AND PASSENGERS EVACUATED. INVESTIGATION REVEALED THAT THE NR 1 FUEL FILTER DRAIN VALVE WAS DEFECTIVE AND ALLOWED THE BOOST PUMP PRESSURED FUEL TO LEAK OUT THROUGH THE DRAIN.   NR 2 ENGINE FLAMED OUT BECAUSE WHEN NR 1 BOOST PUMP WAS SHUTOFF THE CROSSFEED VALVE OPEN1G71 4U4  U  H4SW    E22EA                
20061019001442006101900144SW  2006       10         19         CA060907005      120060830G6730205076031003    ACTUATOR                                BELL  205   205A1       1181414SW  LYC   T53   T5317A      41549NE                              TAIL ROTOR SERVOFAILED          W      A   UNSCHED LANDING                                                                                 FJ FLT CONT AFFECTED         WARNING INDICATION                                  NRNOT REPORTED   1                      CA            180                                                       (CAN) DURING LONG LINE SLINGING OPERATIONS, UPON APPROACHING A DROP ZONE WITH A LOAD. THE COLLECTIVE WAS RAISED TO CUSHION LANDING OF THE LOAD, THEN LOWERED TO TAKE TENSION OFF OF THE LINE. THE HELICOPTER TURNED TO THE LT AND THE RT TAIL ROTOR PEDAL WAS FOUND TO BE STUCK. THE LOAD WAS ALREADY ON THE GROUND AND SUBSEQUENTLY RELEASED. THE COLLECTIVE WAS THEN AGAIN RAISED UNTIL THE AIRCRAFT STOPPED ROTATING AND FWD FLIGHT COULD BE ACHIEVED. THE HELICOPTER MAINTAINED FWD FLIGHT WHILE THE P/C CONTINUED OPERATING THE COLLECTIVE AND TAIL ROTOR CONTROLS. THE LT PEDAL INPUT WAS FINE BUT THE RT PEDAL INPUT WAS AT FIRST JAMMED, THEN BEGAN TO OPERATE WITH RESISTANCE LIKE A HYDRAULIC FAILURE. THE HYDRAULIC ON/OFF SWITCH WAS1G71 4U4  U  H1SW    E17EA                
20061019001452006101900145EU  2006       10         19         CA060907006      120060125G7931                TRANSMITTER                             SNIAS 350   AS350BA     8680817EU  TMECA ARRIELARRIEL1B    6OO30NE                              ENG OIL PRESSUREMALFUNCTIONED   W      O   OTHER                                                                                           N  FALSE WARNING                                                                 CRCRUISE         1                      CA       292                                                            (CAN) PILOT INDICATED THE PRESSURE INDICATOR WAS FLUCTUATING.  TROUBLESHOOTING DETERMINED IT WAS PRESSURE TRANSMITTER.  (TC NR 20060907006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1G71 3U3  UNCH9EU    E19EU                
20061019001472006101900147CE  2006       10         19         CA060907007      120060829G29101013880167      LINE                                    BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE  HARTZLHCE4A HCE4A3I     NE  HYD SYSTEM      LEAKING         W      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) PILOT REPORTED THAT LANDING GEAR DID NOT RETRACT. 2.5 QUARTS OF HYDRAULIC FLUID WERE LOST AND HYDRAULIC PUMP CIRCUIT BREAKER POPPED AND LOW FLUID LEVEL CAUTION LIGHT ILLUMINATED. MANUAL EXTENSION WAS CARRIED OUT AND AIRCRAFT LANDED SAFELY. INVESTIGATION REVEALED RT MAIN LANDING GEAR HYDRAULIC RETRACT LINE WAS LEAKING. THE LINE WAS REPLACED, HYDRAULIC SYSTEM REPLENISHED, GEAR SWINGS CARRIED OUT AND LEAK CHECKED SERVICEABLE. HYDRAULIC LINE P/N 101-388016-7 WAS PRESSURE TESTED ON BENCH AND FOUND TO HAVE A HOLE ONE INCH FROM SWAGED FITTING. THE MFG RECOMMENDED INSPECTION CRITERIA FOR TEFLON COATED HYDRAULIC LINES CALL FOR A VISUAL INSPECTION FOR DETERIORATION AND LEAKS; HOWEVER THE OUTER  SHEATHING PREVENTS S2L72 4T4  TRTA24CE   E26NE   5  CP10NE    
20061019001502006101900150EA  2006       10         19         CA060907008      120060826G5250                LOCK                                    CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              COCKPIT DOOR    MALFUNCTIONED   W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) APPROXIMATELY 10 MINUTES PRIOR TO DESCENT, CALLED THE FLT ATTENDANT TO ENTER AND STAY IN THE FLIGHT DECK AS I WENT TO THE LAV. AFTER RETURNING AND ACTIVATING THE DOOR LOCK CODE THE FLIGHT ATTENDANT HAD PROBLEM UNLOCKING THE DOOR. THE FIRST OFFICER NOW HELPED AND ALSO NOT ABLE TO UNLOCK THE DOOR. I ALSO VERIFIED AND DISCUSSED ALL POSSIBLE OPTIONS VIA THE INTERPHONE. IT WAS DECIDED TO PULL THE DOOR PINS TO OPEN THE DOOR. AFTER RETURNING TO OUR POSITIONS, RESECURED THE DOOR IN POSITION WITHOUT PINS AS NOT TO TRAP OURSELVES IN THE FLIGHT DECK IN THE EVENT OF AN EVACUATION. THE FLIGHT ATTENDANT JUMP SEAT WAS PUT INTO PLACE AS TO CREATE A BARRIER. AFTER LANDING MAINTENANCE WAS CALLED WHO RESECURED THE DOOR AND 2L72 4F4  FRTA21EA   E15NE                
20061019001512006101900151CE  2006       10         19         CA060908001      120060908G301029S7D517515     BOOT                                    CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE  HARTZLHCB3T HCB3TN3     GL  DEICE SYS       DISTORTED       W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       135                                                            (CAN) THE CARGO POD DEICER BOOT EXHIBITS DETERIORATION DUE TO OIL/FUEL CONTAMINATION. SUSPECTED CAUSE IS LEAKING OR OPEN STOP COCKS ON THE ENGINE DRAINS. (TC NR 20060908001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3T3  T  A37CE   E4EA    6  CP15EA    
20061019001532006101900153CE  2006       10         19         CA060908002      120060907G3243MS28775011      O-RING          BEECH                   BEECH 100   100BEECH    1152916CE  PWA   PT6   PT6A28           EA  HARTZLHCD4N3HCD4N3A     GL  CHECK VALVE     CUT             W      O   OTHER                                                                                           O  OTHER                                                                         LDLANDING        1                      CA       10222                                                          (CAN) REF. SDR NR 20060907002  RT BRAKE LOCKED-UP PREVIOUS SDR SUBMITTED MENTIONED THE PARK BRAKE VALVE AS THE UNSERVICEABLE PART, HOWEVER THE NEXT FLIGHT THE BRAKES ON THE RT SIDE LOCKED-UP AGAIN, BRAKES INSPECTED, PRESSURE RELIEVED AND AIRCRAFT RETURNED TO BASE FOR TROUBLSHOOTING, FOUND CO-PILOT RT BRAKE MASTER CYLINDER TRAPPING PRESSURE IN THE SYSTEM, BRAKE CYLINDER REMOVED AND EXAMINED, FOUND O-RING ON CHECK VALVE CUT, O-RINGS IN MASTER CYLINDER REPLACED WITH NEW, FUNCTION TEST CARRIED-OUT, BRAKES OPERATED NORMALLY  (O-RING P/N MS28775-011) (TC NR 20060908002)                                                                                                                                                      1L72 3T4  T  A14CE   E4EA    5  CSTC      
20061019001552006101900155EU  2006       10         19         CA060909001      120060906G5610NAS1581C3T11    SCREW                                   PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  WINDSCREEN      LOOSE           W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA                                                                      (CAN) DURING A SCHEDULEDED PRESSURIZATION CHECK LEAKS WHERE NOTED FROM THE WINDSCREEN ATTACHMENT SCREWS.  ATTACHMENT SCREWS RE-TORQUED WHICH REVEALED THAT SEVERAL WERE LOOSE.  ALTHOUGH THIS IS NOT AN UNHEARD OF SITUATION IT SEEMS TO BE HAPPENING MORE AND MORE.  2 MORE SDRS WILL BE ENTERED FOR SIMILAR ISSUES.   NO OTHER PROBLEMS WERE ENCOUNTERED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060909001)                                                                                                                                                                                                                                                                                                                        1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20061019001562006101900156EU  2006       10         19         CA060909002      120060908G5610NAS1581C3T11    SCREW                                   PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  WINDSCREEN      LOOSE           W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA                                                                      (CAN) DURING A SCHEDULEDED PRESSURIZATION CHECK LEAKS WHERE NOTED FROM THE WINDSCREEN ATTACHMENT SCREWS.  ATTACHMENT SCREWS RE-TORQUED WHICH REVEALED THAT SEVERAL WERE LOOSE.  ALTHOUGH THIS IS NOT AN UNHEARD OF SITUATION IT SEEMS TO BE HAPPENING MORE AND MORE.  2 MORE SDRS WILL BE ENTERED FOR SIMILAR ISSUES.   NO OTHER PROBLEMS WERE ENCOUNTERED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060909002)                                                                                                                                                                                                                                                                                                                        1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20061019001592006101900159EU  2006       10         19         CA060909003      120060823G5610NAS1581C3T11    SCREW                                   PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  WINDSCREEN      BACKED OUT      W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) ON A WALKAROUND SEVERAL WINDSCREEN ATTACHMENT SCREWS WERE NOTED AS BEING PARTIALLY BACKED OUT.  ALL ATTACHMENT SCREWS RE-TORQUED AND SEVERAL MORE WERE FOUND TO BE LOOSE.   SCREWS RETORQUED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20060909003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20061213001402006121300140CE  2006       12         13         CA060911001      120060909G3260                INDICATOR                               BEECH 1900  1900C       1154161CE  PWA   PT6   PT6A65B     52043EA  HARTZLHCB4M HCB4MP3     GL  MLG             INOPERATIVE     W      O   OTHER                                                                                           P  NO WARNING INDICATION                                                         APAPPROACH       1                      CA                                                                      (CAN) DURING FLIGHT TRAINING GEAR WAS EXTENDED. THERE WAS NO RT MAIN GEAR DOWN AND LOCKED LIGHT. AN EMERGENCY GEAR EXTENSION WAS CARRIED OUT. RT MAIN GEAR LIGHT STILL NOT ILLUMINATED. LAMP TEST CARRIED OUT WITH GEAR HANDLE RED INTRANSIT LIGHT ILLUMINATED. PILOTS WERE UNABLE TO REMOVE LIGHT HOLDER TO INSPECT BULBS.  EMERGENCY LANDING DECLARED. LANDING GEAR VISUALLY CHECKED DURING A CIRCUIT BY MAINTENANCE PERSONNEL. GEAR APPEARED DOWN AND LOCKED. AIRCRAFT LANDED WITHOUT EVENT. MAINTENANCE PERSONNEL INSTALLED GEAR PINS AND TOWED AIRCRAFT BACK TO HANGER. FAULTY BULB REPLACED AND SEVERAL GEAR SWINGS CARRIED OUT. NO FAULTS FOUND. THIS PROBLEM COULD HAVE BEEN LESS EVENTFUL IF THE PILOTS WERE MORE EASILY ABLE TO REMOVE2L72 4T4  TRTA24CE   E4EA    6  CP56GL    
20070507001812007050700181WP  2007       5          7          CA060911002      120060724G2810                FUEL FILTER                             GRUMANTS2   TS2ACALFORST3951102WP  PWA   PT6   PT6A67A     52043NE  HARTZLHCB5M HCB5MA3     GL  ENGINE          CONTAMINATED    W      K   NONE                                                                                            C  F.O.D.                                                                        ININSP/MAINT     1                      CA                                                                      (CAN) DURING A ROUTINE 100 HOUR INSPECTION, A LARGE AMOUNT OF PARTICLES WERE FOUND IN THE MAIN FUEL FILTERS AND THE FUEL PUMP INLET FILTERS. THE PARTICLES WERE SENT TO A LAB AND IT WAS DETERMINED THAT IT WAS ORGANIC MATERIAL SIMILAR TO THE EXPLOSION SUPPRESSANT FOAM USED IN THE PYLON FUEL TANKS. THE FOAM HAS BEEN REMOVED, SYSTEM FLUSHED AND NEW FOAM INSTALLED. THE REMAINDER OF THE FLEET (9 AIRCRAFT TOTAL) WILL HAVE THE FOAM REPLACED DURING WINTER MAINTENANCE. (TC NR 20060911002)                                                                                                                                                                                                                                             2H72 4R4  T  A25WE   E26NE   6  CP44GL    
20061019001642006101900164NM  2006       10         19         CA060911006      120060908G3320AL845T279       LAMP                                    AMD   FALC50FALCON2000  2730170NM                                                               LAVATORY        MELTED          W      K   NONE                                                                                            B  SMOKE/FUMES/ODORS/SPARKS                                                      ININSP/MAINT     1                      CA                                                                      (CAN) WHILE PERFORMING THE POST FLIGHT INSPECTION, A ELECTRICAL BURNING ODOR WAS DETECTED IN THE AFT AREA OF THE CABIN. APON FURTHER INSPECTION ONE OF THE LAVATORY MIRROR VANITY LIGHTS WAS FOUND TO BE INOP. WHEN THE BULB WAS REMOVED TO BE REPLACED IT WAS NOTICED THAT ONE END OF THE LAMP ASSEMBLY HAD STARTED TO MELT. WITH THE DEFECTIVE LAMP ASSEMBLY REMOVED IT WAS ALSO NOTED THAT THE DEFECTIVE PN WAS WRONG. INSTALLED WAS A AL-845-T-279 BUT IAW THE FALCON IPC THE LAMP ASSEMBLY SHOULD HAVE BEEN A AL-845-T-279-F. AFTER THE DEFECTIVE LAMP ASSEMBLY WAS REMOVED THE ELECTRICAL BURNING SMELL IN THE CABIN WAS NOT DETECTED ANYMORE. THE CORRECT LAMP ASSEMBLY WAS ORDERED AND THE AIRCRAFT HAS BEEN RETURNED TO SERVICE. (TC NR2K72 4F    RTA50NM                        
20061019001652006101900165NE  2006       10         19         CA060912001      220060912G7250BRH20351        TURBINE BLADES                          BOEING717   717200      1383700NM  RROYCEBR700 BR700715A130     NE                              ENGINE          FRACTURED       W      EC  ENGINE SHUTDOWN         ABORTED TAKEOFF                                                         R  PARTIAL RPM/PWR LOSS                                                          TOTAKEOFF        1                      CA       13801                              13322                       (CAN) IN CLIMB AT 11000 FT PILOT REPORTED LOUD BANG. TGT ROSE  TO 1194 DEG.  PILOT SHUT DOWN ENGINE. AND TURNED BACK. FOUND HEAVY METAL CONTAMINATION IN THE TAIL PIPE.  EMERGENCY LANDING CONDUCTED WITHOUT INCIDENT. ENGINE PRESENTLY AT RRC FOR REPAIR, STRIP OF ENGINE REVEALED HP1 TURBINE BLADES FAILURE BELOW INNER PLATFORM AND SEVERE SECONDARY DAMAGE IN LP TURBINE MODULE. ENGINE IS HIGH TIME TSN;13801 HOURS, CSN; 9396 AND THIS IS FIRST SHOP VISIT. FAILED BLADES HAVE BEEN SHIPPED TO THE OEM (GERMANY) FOR INVESTIGATION.  (TC NR 20060912001)                                                                                                                                                                                 2L72 4F4  FTRA6WE    E00061EN             
20061019001662006101900166    2006       10         19         CA060913001      420060816G611305522311        BULKHEAD        CESSNA                  CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA  MCAULY1A170 1A170E      GL  SPINNER         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       492                                                            (CAN) DURING CHANGEOVER FROM FLOATS TO WHEELS, AND DURING THE CHANGE FROM SEAPLANE PROP TO WHEELPLANE PROP , CLOSER INSPECTION OF THE FORWARD PROP SPINNER BULKHEAD REVEALED NUMEROUS CRACKS. THESE CRACKS WERE RADIATING FROM THE PROP ATTACHMENT BOLT HOLES, TO THE BEND RADIUS OF THE BULKHEAD (P/N 0552231-1). CRACKS WERE ALSO AROUND THE RADIUS WHERE THE PROP BOLT WASHERS MEET AGAINST THE SPINNER PLATE. AIRCRAFT HAD FLOWN 157.1 HRS ON FLOATS WITH NUMEROUS TAKEOFFS AND LANDINGS DURING FLOAT FLIGHT TRAINING. THIS SPINNER PLATE WAS LAST CHANGED 492.0 HRS AGO AFTER IT HAD AGAIN BEEN CHANGED OVER FROM FLOATS TO WHEELS. AT THAT TIME, THE PLANE HAD LOGGED 222.1 HRS OF FLOAT FLIGHT TRAINING, AND CRACKS WERE ALSO APPARENT AT1H71 3O3  ONT3A12    1E10    5  NP857     
20061019001672006101900167CE  2006       10         19         CA060913002      120060816G322005412024        BUSHING                                 CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA  MCAULY1A170 1A170E      GL  NLG             SEPARATED       W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2578                                                           (CAN) THE MAIN GEAR LEG BUSHINGS ARE A STEEL OUTER TUBE, WITH A THICK INNER URETHANE CENTER.  DURING PROGRESSIVE CARE OPERATION NR 1, INSPECTION OF THE RT MAIN GEAR LEG REVEALED THAT THE URETHANE INNER BUSHING MATERIAL HAD DEPARTED FROM THE OUTER STEEL BUSHING (P/N 0541202-4).  IT HAD MOVED LOOSELY ALONG THE TUBULAR GEAR LEG TOWARDS THE CENTER OF THE AIRCRAFT. THIS ALLOWED THE TUBULAR GEAR LEG TO RATTLE ON THE INSIDE OF THE STEEL OUTER BUSHING. THE STEEL OUTER BUSHING IS HELD IN PLACE WITH 2 (C) CLIPS, HOWEVER THE URETHANE INNER PART OF THE BUSHING LOOKS TO BE ONLY A PRESS FIT. THE AIRCRAFT WAS JACKED UP, THE LEG WAS REMOVED, AND A NEW BUSHING WAS INSTALLED. THE OTHER 3 MODEL AIRCRAFT IN THE FLEET HAVE BEEN INS1H71 3O3  ONT3A12    1E10    5  NP857     
20070507000862007050700086SW  2007       5          7          CA060913003      120060912G530280011P12F20     SKIN            BELL                    BELL  206   206B        1181511SW  ALLSN 250C  250C20      03013GL                              TAILBOOM        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       15442                                                          (CAN) WHILE CARRYING OUT ASB 206-06-107, FIN WAS REMOVED AND A FIN ATTACHMENT INSERT P/N 80-011-P12F2-0 WAS FOUND CRACKED. AFTER REMOVAL OF THE CRACKED INSERT, THE IB SKIN BELOW WAS FOUND TO HAVE SEVERAL CRACKS PROPAGATING UNDERNEATH THE DOUBLER. THE IB DOUBLER WAS REMOVED AND A TOTAL OF APPROXIMATELY 6 CRACKS WAS FOUND, ONE OF WHICH WAS 3 INCHES IN LENGTH. THE FIN WAS REPLACED. (TC NR 20060913003)                                                                                                                                                                                                                                                                                                                               1G71 3U3  U  H2SW    E4CE                 
20061019001682006101900168EA  2006       10         19         CA060913004      120060906G2810215640015       FUEL CELL                               CNDAIRCL215 CL2156B11215       EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  WING            LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       1414                                                           (CAN) A/C DEVELOPED A FUEL LEAK. LEAK WAS MEASURED AND FOUND TO BE THE DRIP TYPE AND COMING FROM THE WING TIP AREA.UPON INSPECTION IT WAS DETERMINED THAT THE FUEL LEAK WAS COMING FROM THE RT FUEL CELLS. DUE TO PREVIOUS REPLACEMENT OF CELLS NR 3 THROUGH NR 8 IT WAS DETERMINED TO TEST CELLS NR 1 AND 2.  BOTH CELLS WERE FOUND LEAKING AND SUBSEQUENTLY REPLACED. A/C GROUND CHECKED OK. P/N 215-64001-5 SERIAL NR 72672 NR 1 CELL P/N 215-64002-8 SN 72872 NR 2 CELL (TC NR 20060913004)                                                                                                                                                                                                                                                 2H72 4T4  TRTA14EA   E20NE   6  CP7NE     
20070507000872007050700087SW  2007       5          7          CA060913005      120060911G7921212030041233    SUPPORT                                 BELL  412   412         1182202SW                                                               OIL COOLER      OBSTRUCTED      W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) SUPPORT 212-030-041-233 FOULS WITH TRANSMISSON OIL LINE 212-040-229-001. (TC NR 20060913005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1G72 4U      H4SW                         
20061019001692006101900169EU  2006       10         19         CA060913006      120060913G324640424           WHEEL                                   PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  MLG             DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       6024                                                           (CAN) DURING AN INSPECTION WHEEL ASSY WAS REMOVED, GREASE COVER FOR THE BEARING AND BEARINGS REMOVED FOR INSPECTION/ REPACKING. THE WHEEL WAS THEN CLEANED AND INSPECTED FOR WEAR.  AT THAT POINT IT WAS NOTICED THAT THE WHEEL HOUSING HAD SEVERAL DEEP GROOVES WHERE THE GREASE COVER SITS.  WE HAVE NOTICED THIS PROBLEM ON OTHER WHEEL ASSY BUT TO A LESSER DEGREE. WE HAVE SENT AN E-MAIL TO MFG AND INFORMED THEM OF THIS PROBLEM. (TC NR 20060913006)                                                                                                                                                                                                                                                                                    1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20061019001702006101900170EU  2006       10         19         CA060914001      120060911G3150                WARNING MESSAGE                         AEROSPATR42 ATR42300    8680920EU  PWA   120   PW120            NE  HAMSTD14SF  14SF5       NE                  MULTIPLE IND    W      A   UNSCHED LANDING                                                                                 GJ MULTIPLE FAILURE          WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) AFTER DEPARTING THE CREW OBSERVED NR 1 ADC, NR 1 ENGINE ANTI-ICE AND NR 1 PROP DEICE FAULTS. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WITHOUT INCIDENT. MAINTENANCE TROUBLE SHOOTING  WAS UNABLE TO DUPLICATE THE FAULT. AFTER SATISFACTORY OPERATIONAL TESTING OF THE AFFECTED SYSTEMS THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20060914001)                                                                                                                                                                                                                                                                                                                                                                                      2H72 4T4  TRTA53EU   E20NE   6  CP7NE     
20070507000902007050700090SW  2007       5          7          CA060914002      120060906G5302                STRUCTURE       BELL                    BELL  407   407         1182206SW                                                               TAILBOOM        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       9257       53247                                               (CAN) APPROX. 8 IN. CRACK FOUND IN TAILBOOM NEAR THE 5TH HANGER BEARING  APPROX. 270 HRS REMAINING OUT OF THE 5000 HRS RETIREMENT LIFE. (TC NR 20060914002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1G71 3U    O H2SW                         
20061019001712006101900171CE  2006       10         19         CA060914003      120060808G2497                CONNECTOR       FORD                    CESSNA172   172R        2072401CE  LYC   IO360 IO360L2A         EA  MCAULY1C235 1C235LFA    GL  ALTERNATOR      BROKEN          W      BA  EMER. DESCENT           UNSCHED LANDING                                                         HP ELECT. POWER LOSS-50 PC   NO WARNING INDICATION                               CRCRUISE         1                      CA       4075       R204620                                             (CAN) ALTERNATOR FAILURE WHILE ON ROUTE TO DESTINATION WAS CAUSED BY AN AMP CONECTOR LOOP END BREAKING OFF AND CAUSING LOSS OF ELECTRICAL POWER AND A SHORT IN THE SYSTEM. (TC NR 20060914003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H71 3O3  ONT3A12    1E10    5  NP12EA    
20061019001722006101900172CE  2006       10         19         CA060914004      120060914G251007190131        SEAT BACK                               CESSNA172   172R        2072401CE  LYC   IO360 IO360L2A         EA  MCAULY1C235 1C235LFA    GL  COCKPIT SEAT    BROKEN          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       4089                                                           (CAN) CO PILOTS SEAT BACK WAS FOUND BROKEN ABOUT 2 INCHES ABOVE THE WELDED JOINT ON THE LT SIDE OF THE SEAT BACK. BROKEN PART REMOVED NEW SEAT BACK FRAME ON ORDER WITH CESSNA. (TC NR 20060914004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3O3  ONT3A12    1E10    5  NP12EA    
20070507000912007050700091WP  2007       5          7          CA060915001      120060914G7820C1963           MUFFLER                                 ROBSINR44   R44         7640120WP  LYC   O540  O540F1B5    41532EA                              EXHAUST         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1939                                                           (CAN) WHILE PERFORMING CF90-3R2 ON THE MUFFLER ASSEMBLY THE EXHAUST SHROUD WAS REMOVED AND A (2) INCH CRACK WAS FOUND WHERE THE EXHAUST PIPE JOINS THE MUFFLER. (TC NR 20060915001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1G71 3O3  O  H11NM   E295                 
20061019001732006101900173NE  2006       10         19         CA060915002      220060914G73142043M12P03      SHAFT                                   EMB   ERJ190ERJ190100IGW3260408EU  GE    CF34  CF34*            NE                              FUEL PUMP       BROKEN          W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA       159                                994203                      (CAN) DURING CRUISE AT FL360, THE NR 1 ENGINE FAILED.  THE CREW DECLARED AN EMERGENCY AND BEGAN DESCENT.  DURING THE DESCENT A RE-START WAS ATTEMPTED BUT WAS UNSUCCESSFUL.  THE FLIGHT DIVERTED AND LANDED APPROX 400 KG OVERWEIGHT. (TC NR 20060915002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F4  FRTA57NM   E15NE                
20061019001742006101900174EA  2006       10         19         CA060918001      120060918G2750                FLAP SYSTEM                             CNDAIRCL601 CL6012A12   1900303EA  GE    CF34  CF343A      30015NE                              TE FLAPS        MALFUNCTIONED   W      C   ABORTED TAKEOFF                                                                                 FJ FLT CONT AFFECTED         WARNING INDICATION                                  TOTAKEOFF        1                      CA                                                                      (CAN) FLAP FAILED ON TAKEOFF, A/C RETURNED AND LANDED SAFELY AT QB MAIN BASE, BREAKER WAS RESET IAW OPERATING MANUAL, COULDN`T DUPLICATED THE SNAG. A/C DID ONE FLIGHT AND RETURN TO BASE WITHOUT ANY SNAG.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA21AE   E15NE                
20061019001762006101900176    2006       10         19         CA060918002      420060912G3100285T003117      CIRCUIT CARD                            BOEING767   767375      1385217NM  GE    CF6   CF680C2*         GL                              COCKPIT         MALFUNCTIONED   W      C   ABORTED TAKEOFF                                                                                 N  FALSE WARNING                                                                 TOTAKEOFF        1                      CA                                                                      (CAN) CAPTAIN REJECTED TAKEOFF ROLL AT 155KTS BECAUSE OF A (TAKEOFF CONFIGURATION SAFETY WARNING) MESSAGE, 4 MAIN LANDING GEAR TIRES REPLACED DUE TO HIGH ENERGY BRAKING AND FUSE PLUGS MELTING. NEW LANDING CONFIGURATION CARD INSTALLED AND TESTED. (TC NR 20060918002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F4  FRTA1NM    E23EA                
20061213001412006121300141GL  2006       12         13         CA060918003      120060829G52102256136100      HOOK            DIAMON                  DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO  SNSNCHW69EK W69EK63     EA  CANOPY          CRACKED         W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA       2175                                                           (CAN) PILOT NOTICED CANOPY LIGHT ON IN FLIGHT AND RETURNED FOR LANDING. INSPECTION REVEALED THAT THE CANOPY LATCH PLATE ( P/N 22-5613-61-00) ON THE LT SIDE WAS BROKEN ALLOWING THE CANOPY LIGHT TO BE ILLUMINATED. 2 MICRO SWITCHES ARE USED TO TURN THE WANING LIGHT OFF ONLY WHEN BOTH LATCHES ARE FULLY CLOSED. THE SYSTEM WORKED PROPERLY WHEN ONE LATCH FAILED. SERVICEABLE LATCH INSTALLED AND SYSTEM CHECKED AND ADJUSTED IAW  MM (DMM) AS REQUIRED. AIRCRAFT RELEASED. THE SYSTEM IS INSPECTED EVERY 100 HR, WHICH REQUIRES A PULL TEST TO BE CARRIED OUT FOR FRICTION VERIFICATION AND ADJUSTMENT AS REQUIRED. STRESS CAN BE APPLIED TO THE LATCH HOOK IF THE CANOPY IS ACCIDENTALLY CLOSE WITH THE LATCH IN THE CLOSED POSITION OR IF1L71 3O3  ONTTA4CH   E7SO    5  NTA4CH    
20061019001772006101900177SO  2006       10         19         CA060918004      120060909G7120LW38275         BOLT                                    PIPER PA44  PA44180     7104402SO  LYC   O360  O360E1A6    41514EA  HARTZLHCC2Y HCC2YR2     GL  ENGINE MOUNT    BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            1446                                                      (CAN) DURING ROUTING INSPECTION IT WAS NOTED THAT ONE OF THE BOLTS SECURING THE RT BOTTOM ENGINE MOUNT BRACKET ONTO THE CRANKCASE OF THE RT ENGINE WAS BROKEN AND THE OTHER BOLT WAS LOOSE. BROKEN TREADED BOLT PIECE WAS REMOVED FROM CRANKCASE AND A SERVICEABLE BRACKET INSTALLED DUE TO ELONGATED HOLES IN OLD UNIT. TOP RT BRACKET WAS ALSO FOUND LOOSE, BRACKET REMOVED AND VISUALLY INSPECTED, NO DAMAGE FOUND. BRACKET REINSTALLED. ALL 6 ENGINE MOUNTING BRACKET BOLTS REPLACED AND TORQUED. BOLT TORQUE TO BE RECHECKED NEXT INSPECTION.  ALTHOUGH THE ENGINE HAD 1445.6 HRS SINCE LAST OVERHAUL IT IS NOT MANDATORY ACCORDING TO MFG SB 240T TO REPLACE THESE BOLTS. (TC NR 20060918004)                                             1L72 3O3  O  A19S0   E286    5  CP920     
20061019001782006101900178GL  2006       10         19         CA060918005      120060908G8011656762          GEAR                                    DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO  SNSNCHW69EK W69EK63     EA  STARTER         WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       28                                 650199                      (CAN) DURING THE FIRST 25/100 HR INSPECTION ON THIS AIRCRAFT, INSPECTION OF THE OIL SYSTEM REVEALED CONTAMINATION ON THE DRAIN PLUG MAGNET AND OIL FILTER. SUBSEQUENTLY, THE STARTER WAS REMOVED FOR CLUSTER AND DRIVE GEAR INSPECTION. THE STARTER AND CLUSTER GEARS WERE FOUND DAMAGED IN THE AREA OF INITIAL STARTER ENGAGEMENT. THE DAMAGE EXCEEDED THE NORMAL WEAR DESCRIBED IN SB04-07. BOTH STARTER AND CLUSTER GEARS WERE REPLACED. (TC NR 20060918005)                                                                                                                                                                                                                                                                                 1L71 3O3  ONTTA4CH   E7SO    5  NTA4CH    
20061019001792006101900179GL  2006       10         19         CA060918006      120060915G8011656762          GEAR                                    DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO  SNSNCHW69EK W69EK63     EA  STARTER         WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       37                                 650197                      (CAN) DURING TROUBLESHOOTING OF THE FUEL SYSTEM DUE TO ENGINE QUITTING ON ROLL OUT FROM LANDING, THE ENGINE FUEL SYSTEM WAS BEING CHECKED IAW SID97-3C, AT WHICH TIME DURING A GROUND RUN IT WAS NOTICED THAT OIL PRESSURE HAD DROPPED TO ALMOST (0). THE ENGINE WAS SHUTDOWN IMMEDIATELY.  FURTHER INSPECTION OF THE LOSS OF OIL PRESSURE REVEALED METAL CONTAMINATION ON THE OIL PRESSURE RELIEF VALVE. FURTHER INSPECTION OF THE OIL SYSTEM REVEALED MORE CONTAMINATION ON THE DRAIN PLUG MAGNET AND OIL FILTER. SUBSEQUENTLY THE STARTER WAS REMOVED FOR CLUSTER AND DRIVE GEAR INSPECTION. THE STARTER AND CLUSTER GEARS WERE FOUND DAMAGED IN THE AREA OF INITIAL STARTER ENGAGEMENT. THE DAMAGE EXCEEDED THE NORMAL WEAR DESCRIBED IN SB01L71 3O3  ONTTA4CH   E7SO    5  NTA4CH    
20061019001802006101900180SO  2006       10         19         CA060918007      220060915G731464936849A1      PUMP                                    DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO                              FUEL SYS        OUT OF ADJUST   W      D   RETURN TO BLOCK                                                                                 YJ ENGINE STOPPAGE           WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA       37                                 650197                      (CAN) PILOT REPORTED ENGINE QUIT ON TOUCH DOWN, ABLE TO RESTART. FUEL INJECTION SYSTEM CHECKED IAW SID97-3C AND ADJUSTED. BOTH INLINE FUEL FILTERS INSPECTED FOR CONTAMINANTS, CLEANED AND RE-INSTALLED. SMALL AMOUNT OF CONTAMINANTS FOUND IN INLINE FILTER AFTER THE MECHANICAL FILTER. AIRCRAFT RELEASED CONDITIONAL TO SATISFACTORY TEST FLIGHT. AIRCRAFT TEST FLIGHT CARRIED OUT SATISFACTORY. A SISTER AIRCRAFT HAS REPORTED A SIMILAR DEFECT. AN SDR WILL BE SUBMITTED AFTER TROUBLESHOOTING IS COMPLETED. TROUBLESHOOTING IS BEING CARRIED OUT BY DIAMOND AIRCRAFT. THESE 2 AC EQUIPED WITH NEW ALTITUDE COMPENSATION FUEL PUMPS. (TC NR 20060918007)                                                                                   1L71 3O3  ONTTA4CH   E7SO                 
20061019001812006101900181EA  2006       10         19         CA060918009      120060916G783022850809119     TRACK                                   CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30068NE                              THRUST REVERSER CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       24451                                                          (CAN) NR 2 ENGINE LT LOWER THRUST REVERSER TRACK FOUND CRACKED DURING A C-CHECK INSPECTION. PART REPLACED AS A MAIN TRACK ASSEMBLY P/N 228-50809-801.   REFERENCE :MFG CSP A-006 IPC CHAP 78-34-11 FIGURE 1 , ITEM 75A AND 95A. (TC NR 20060918009)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F4  FRTA21EA   E15NE                
20061019001822006101900182NM  2006       10         19         CA060918010      120060913G801297907021        START VALVE                             BOEING727   727225      1384077NM  PWA   JT8   JT8D9       52048NE                              ENGINE          MALFUNCTIONED   W      O   OTHER                                                                                           N  FALSE WARNING                                                                 NRNOT REPORTED   1                      CA                                                                      (CAN) THE NR 3 ENGINE START VALVE OPEN LIGHT ILLUMINATED DURING CLIMB OUT.  A/C RETURNED TO BASE.   A/C INSPECTED AND THE START VALVE REPLACED DUE CRACKED.  A/C RETURNED TO SERVICE. FAULT REOCCURRED DURING CLIMB.  A/C RETURNED TO BASE.   THE FUEL HEAT DUCT WAS FOUND CRACKED CAUSING WIRING DAMAGE (HEAT) AND THE START VALVE INDICATION. DETAILED ENGINE INSPECTION CARRIED OUT. THE FUEL HEAT DUCT WAS REPLACED AND AIRCRAFT WIRING REPAIRED AS REQUIRED.  A/C RETURNED TO SERVICE.  (TC NR 20060918010)                                                                                                                                                                                                                                2L73 4F4  F  A3WE    E2EA                 
20061019001832006101900183EA  2006       10         19         CA060918011      120060906G3246L312111         BEARING                                 DHAV  DHC8  DHC8311     1386006EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF23      NE  MLG WHEEL       DAMAGED         W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA       8944                                                           (CAN) AT TIRE CHANGE, DURING WHEEL AND BEARING INSPECTION FOUND THE OUTER WHEEL OUTER BEARING CUP, WITH A PLATING SURFACE MISSING (.3750 INCH X .2500 INCH) AND ROLLER BEARING P/N L81214 * 2-629 THAT MATCH THIS CUP WITH LITTLE MARK ON ROLLER. WHEEL AFT VISUALLY INSPECTED AND FOUND OK. (TC NR 20060918011)                                                                                                                                                                                                                                                                                                                                                                                                                                2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20061019001842006101900184NE  2006       10         19         CA060919001      220060916G7200                SHUTOFF VALVE                           BOEING727   727233      138408ANM  PWA   JT8   JT8D15      52051NE                              NR 3 ENGINE     LEAKING         W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      CA                                                                      (CAN) DEPARTING THE CREW OBSERVED A STRUT OVERHEAT CONDITION ON NR 3 ENGINE. THE AIRCRAFT DIVERTED WHERE MAINTENANCE DETECTED A LEAK AT THE WING ANTI ICE SHUT-OFF VALVE (SOV). GASKETS WERE REPLACED AND NO FURTHER FAULT APPEARED EVIDENT AT GROUND RUN. DURING THE SUBSEQUENT DEPARTURE THE OVER TEMP CONDITION AT APPLICATION OF TAKE-OFF POWER, THE CREW REJECTED THE TAKE-OFF. MAINTENANCE DETECTED A LEAK AT THE PRE-COOLER WHICH WAS CORRECTED AND CARRIED OUT MULTIPLE TAKE-OFF POWER TESTS WITH NO FAULT INDICATION. THE SUCCEEDING DEPARTURE WAS AGAIN REJECTED AT 60KNOTS DUE TO AN OVERTEMP CONDITION ON NR 3 STRUT. MAINTENANCE REPLACED THE FIRE WIRE LOOP AND CORRECTED AN ADDITIONAL LEAK AT THE PRECOOLER BEFORE RETURNING THE2L73 4F4  FRTA3WE    E2EA                 
20061019001852006101900185CE  2006       10         19         CA060919002      120060918G243530728692        SPLINE                                  LEAR  45    45LEAR      5170805CE  GARRTTTFE731TFE7312     01518WP                              STARTER GEN     CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                          P116176C                    (CAN) ENGINE FAILED TO START.  AFTER INSPECTION FOUND THAT STARTER/GEN SPLINE INSERT HAD CRACKED CAUSING THE SPLINE TEETH TO BREAK OFF.  UNABLE TO DETERMINE IF CRACK HAD OF OCCURRED BEFORE OR AFTER GEAR TEETH HAD BROKEN OFF.  REPLACE SPLINE AND AIRCRAFT STARTED NORMALLY. FLEET INSPECTION TO BE C/O. (TC NR 20060919002)                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTT00008WIE6WE                 
20061019001862006101900186NM  2006       10         19         CA060919003      120060918G3320BV33001215      SOCKET                                  DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF23      NE  CABIN LIGHTS    BURNED          W      F   ACTIVATE FIRE EXT.                                                                              B  SMOKE/FUMES/ODORS/SPARKS                                                      NRNOT REPORTED   1                      CA                                                                      (CAN) AFTER BOARDING WAS COMPLETED AND DOORS CLOSED, CA1 REPORTED A STRONG SMELL OF SMOKE COMBINED WITH LIGHT SMOKE DEVELOPMENT IN THE CABIN. CONTROLLED DISEMBARKATION WAS ORDERED, MAYDAY CALL PERFORMED AND ON GROUND EMERGENCY ITEMS COMPLETED ON THE FLIGHT DECK. AFTER PAX DISEMBARKATION COCKPIT CREW DISCHARGED ONE FIRE EXTINGUISHER INTO THE AREA OF SMOKE DEVELOPMENT AND THEN DISEMBARKED THE A/C. REASON FOR THE SMOKE DEVELOPMENT WAS A SHORT IN THE OVERHEAD LIGHTING SYSTEM. THE FAULT OCCURED ON THE FIRST LT OVERHEAD LAMP HOLDER. HOLDER FOUND BURNED.  (TC NR 20060919003)                                                                                                                                                  2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20061019001872006101900187EA  2006       10         19         CA060919004      120060917G551260021134434     VISOR                                   CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30015NE                              VERTICAL STAB   CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       24451                                                          (CAN) BOTH THE LT AND RT LOWER VISOR ASSEMBLIES WERE FOUND DAMAGED  FROM CRACKING AT THE AFT TOP END. THIS MAY HAVE BEEN DUE TO FLUTTER AT THE AFT END OF THE FAIRING DURING FLIGHT. SINCE IT IS ATTACHED TO THE MOVABLE HORIZONTAL STABILIZER, THERE IS NO FASTENERS AT THAT AFT END OF THE FAIRING. THERE WERE NO VIBRATIONS OR DEFECTS OF THAT THAT NATURE REPORTED ON THIS AIRCRAFT BEFORE IT CAME IN FOR A HEAVY  CHECK DURING  WHICH TIME THIS DAMAGED FAIRINGS WERE FOUND.  HOWEVER THIS DAMAGE IS OFTEN NOTED ON OTHER AIRCRAFT AS WELL AND MAY OR MAY NOT HAVE CAUSED AIRFRAME VIBRATION OR INTERFERENCE WITH  THE MOVING HORIZONTAL STABILIZER. (TC NR 20060919004)                                                                   2L72 4F4  FRTA21EA   E15NE                
20061019001882006101900188EU  2006       10         19         CA060919005      120060910G2760233009          ACTUATOR                                FOKKERF28   F28MK0100   4990807EU  RROYCETAY   TAY65015    54557NE                              SPEED BRAKE     MALFUNCTIONED   W      D   RETURN TO BLOCK                                                                                 O  OTHER                                                                         LDLANDING        1                      CA                                                                      (CAN) FLIGHT CREW REPORTED THAT THE SPEED BRAKE WOULD NOT RETRACT UPON SELECTION TO DO SO. FOLLOWING LANDING.  BOTH PADDLES CONFIRMED OPEN. AIRCRAFT WAS FERRIED TO BASE, WHERE THE SPEED BRAKE ACTUATOR WAS REPLACED. SYSTEM TESTED SERVICEABLE AFTER REPLACEMENT.  SPEED BRAKE ACTUATOR PN 23300-9 SN MC-046 WAS REPLACED MFG SERVICES HAVE REQUESTED THIS ACTUATOR FOR ANALYSIS DUE TO SIMILAR REPORTS FROM OTHER OPERATORS.  ITEM OPEN TO MONITOR THE FOLLOW UP VIA THE QUARTERLY RELIABILITY MEETING.  (TC NR 20060919005)                                                                                                                                                                                                                 2L72 4F4  FRT        E25NE                
20061019001892006101900189EA  2006       10         19         CA060919006      120060916G5610601R3303311     WINDOW                                  CNDAIRCL600 CL6002C10   1390015EA  GE    CF34  CF34*            NE                              COCKPIT         CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA       8346                                                           (CAN) LT SIDE-WINDOW REPLACED IAW AMM.   AERODYNAMIC SEAL INSTALLED AND SEALING PERFORMED. CABIN PRESSURE TEST AND LEAK CHECK PERF, OK. WINDOW HEATING CHECKED, OK. (TC NR 20060919006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRTA21EA   E15NE                
20061019001902006101900190GL  2006       10         19         CA060920001      220060917G7210                GEARBOX                                 LKHEED382   382G        526414USO  ALLSN 501D  501D22A     03006GL  HAMSTD54H   54H60117    NE  NR 2 RGB        MAKING METAL    W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) DEPARTING THE CREW OBSERVED A CHIP LIGHT INDICATION ON NR 2 RGB. THE ENGINE WAS SHUT-DOWN AND THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WITHOUT FURTHER INCIDENT. MAINTENANCE FOUND  CONTAMINATION ON THE RGB PLUG BELIEVED TO BE FROM THE STARTER SEAL. THE SEAL WAS REPLACED AND THE AIRCRAFT RUN AT HIGH POWER SETTING FOR 30 MINUTES WITH NO FURTHER INDICATION. (TC NR 20060920001)                                                                                                                                                                                                                                                                                                                                                2H74 4T4  T  A1SO    E282    6  CP906     
20061019001912006101900191EU  2006       10         19         CA060920002      120060920G2820416113004       LINE                                    SNIAS 350   AS350BA     8680817EU  LYC   LTS101LTS101600A3 41560NE                              FCU             CRACKED         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) GOVERNOR FAIL TO RESPONSE ON TAKE OFF, VISUAL CHECK OF ENGINE COMPARTMENT FOUND CRACKED LINE ON GOVERNOR TO FCU LINE NP TO PR TO PG LINE . LINE REPLACED WITH NEW A/C BACK TO SERVICE. (TC NR 20060920002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1G71 3U3  UNCH9EU    E5NE                 
20061019001922006101900192EU  2006       10         19         CA060920003      120060920G2435150SG116Q       STARTER GEN                             SNIAS 350   AS350BA     8680817EU  LYC   LTS101LTS101600A3 41560NE                              ENGINE          BROKEN          W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA            350                                                       (CAN) GENERATOR LIGHT CAME ON IN FLIGHT, LANDED AND SHOTDOWN, STARTER FOUND BROKEN. STARTER REPLACED AND SENT FOR OVERHAUL. (TC NR 20060920003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1G71 3U3  UNCH9EU    E5NE                 
20061019001932006101900193    2006       10         19         CA060920004      420060918G3422                AHRS                                    AEROSPATR42 ATR42300    8680920EU  PWA   120   PW120            NE  HAMSTD14SF  14SF5       NE  NR 2            FAILED          W      A   UNSCHED LANDING                                                                                 I  FLT. ATTITUDE INST.                                                           CLCLIMB          1                      CA                                                                      (CAN) DURING DEPARTURE THE NR 2 AHRS UNIT FAILED. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE. CURRENTLY AWAITING PARTS. (TC NR 20060920004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2H72 4T4  TRTA53EU   E20NE   6  CP7NE     
20061019001942006101900194CE  2006       10         19         CA060920005      120060814G213352771338        OUTFLOW VALVE                           CESSNA500   560CESSNA   2076750CE  PWA   530   PW535A           NE                              CABIN PRESSURE  FAILED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            DEDESCENT        1                      CA       1545                                                           (CAN) UNCOMMANDED PRESSURIZATION DURING DESCENT OF CABIN AT APPROX 10,000 FEET WHILE IN AUTO MODE - PREVENTING TO  MANUAL MODE WOULD NOT DECREASE RATE OF CABIN DIVE - CREW CONTROLLED CABIN PRESSURIZATION BY CONTROLLING ENGINE BLEED AIR SOURCE VALVES SUPPLYING CABIN AIR. THIS PROBLEM IS CAUSED BY A STICKING OPEN DIVE SOLENOID VALVE IN THE PRIMARY OUTFLOW VALVE ASSEMBLY.  MFG HAS INCORPORATED SB 560-21-27 TO INSTALL A PARTICULATE TRAP IN THE PNEUMATIC LINE TO PREVENT THIS PROBLEM. (TC NR 20060920005)                                                                                                                                                                                                                         2L72 4F4  FRTA22CE   E00053EN             
20061019001952006101900195EA  2006       10         19         CA060920006      120060912G5510                BOLT                                    FOUND FBA   FBA2C       3640102EA  LYC   O540  IO540*      41532EA  HARTZLHCC3Y HCC3YR      GL  HORIZONTAL STAB BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       600                                                            (CAN) UPON REMOVAL OF THE LT FINLET THE REAR ATTACH BOLT (P/N AN3-4A) BROKE. WHEN INSTALLING 4 NEW BOLTS IT WAS NOTICED THAT THE WASHER RODE UP ON THE RADIUS OF THE ATTACH BRACKET CAUSING STRESS ON THE BOLT. WHEN HOLE LOCATION WAS CHECKED AGAINST THE RT FINLET THERE WAS .100 OF AN INCH DIFFERENCE. A SMALL FLAT WAS GROUND IN THE WASHER SO IT WOULD NOT RIDE UP IN THE RADIUS WHEN BOLT INSTALLED. (TC NR 20060920006)                                                                                                                                                                                                                                                                                                                 1H71 3O3  O  A7EA    1E4     5  CP25EA    
20061019001212006101900121EA  2006       10         19         CA060920007      120060413G2434                GENERATOR                               DHAV  DHC6  DHC6        2802606EA  PWA   PT6   PT6A27      52043EA                              NR 2            SHORTED         W      A   UNSCHED LANDING                                                                                 HJ ELECT. POWER LOSS-50 PC   WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) IN CLIMB BOTH GENERATORS TRIPPED OFF LINE AND WOULD NOT RESET. TROUBLE SHOOTING REVEALED AN INTERNAL SHORT IN THE NR 2 GENERATOR THAT CAUSED BOTH GENERATORS TO TRIP THROUGH THE BUSTIE.  SUBMITTER FILE IS ADR 150. (TC NR 20060920007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H72 3T4  TRTA9EA    E4EA                 
20061011001292006101100129SW  2006       10         11         CA060920008      120060918G7714AG44AF          TACH GENERATOR                          SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE33111U   01514WP  MCAULY4HFR344HFR34C652  NE  RT ENGINE       SLIPPED         W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      CA                                                                      (CAN) AIRCRAFT DEPARTED AIRPORT AND UPON CLIMBOUT THE RT ENGINE RPM INDICATION BEGAN TO FLUCTUATE.  ALL OTHER PARAMETERS REMAINED NORMAL.  AIRCRAFT RETURNED AND UPON INVESTIGATION FOUND DRIVE SHAFT INTACT YET SLIPPING INTERNALLY.  TACH GENERATOR REPLACED, RUNUP COMPLETED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20060920008)                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4T4  TRTA8SW    E4WE    6  C3PNE     
20061011001332006101100133EA  2006       10         11         CA060920009      120060906G3213C6UF10151       STRUT                                   DHAV  DHC6  DHC6        2802606EA  PWA   PT6   PT6A27      52043EA                              FRONT FLOAT     BROKEN          W      C   ABORTED TAKEOFF                                                                                 O  OTHER                                                                         TOTAKEOFF        1                      CA                                                                      (CAN) ON TAKEOFF IN ROUGH WATER THE LT FRONT FLOAT STRUT BROKE AT THE UPPER END. STRUT REPLACED. (TC NR 20060920009)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H72 3T4  TRTA9EA    E4EA                 
20061011001342006101100134EA  2006       10         11         CA060920010      120060906G3213C6UF10151       STRUT                                   DHAV  DHC6  DHC6        2802606EA  PWA   PT6   PT6A27      52043EA                              FRONT FLOAT     BROKEN          W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         LDLANDING        1                      CA                                                                      (CAN) ON LANDING IN ROUGH WATER THE RT FRONT FLOAT STRUT BROKE AT THE UPPER END. STRUT REPLACED. (TC NR 20060920010)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H72 3T4  TRTA9EA    E4EA                 
20061011001352006101100135    2006       10         11         CA060920011      420060918G2565                SLIDE                                   AIRBUS320   A320214     3930316EU  CFMINTCFM56 CFM565B4P        NE                              L2 DOOR         UNWANTED DEPLOY W      H   DEACTIVATE SYST/CIRCUITS                                                                        W  INADEQUATE Q C                                                                TXTAXI/GRND HDL  1                      CA                                                                      (CAN) ACCIDENTLY FLIGHT ATTENDANT DEPLOYED THE SLIDE AT L-2 DOOR. INITIALLY SHE WENT TO DEACTIVATE THE DOOR BUT WAS DISTRACTED THEN USED THE OPEN LEVER INSTEAD OF THE DISARM LEVER CAUSING THE INCIDENT. SLIDE WAS DEPLOYED BUT NOT INFLATED, DUE TO THE ACTUATION CABLE FOUND WRAPPED AROUND THE TOP OF CYLINDER WHICH PREVENT THE INFLATION. (TC NR 20060920011)                                                                                                                                                                                                                                                                                                                                                                             2L72 4F4  FRTA28NM   E38NE                
20061011001362006101100136SO  2006       10         11         CA060920013      220060916G8520649134          CRANKSHAFT                              CESSNA206   U206G       2073356CE  CONT  O520  IO520F      17032SO  HARTZLHCJ3Y PHCJ3YF1    GL  ENGINE          BROKEN          W      C   ABORTED TAKEOFF                                                                                 YJ ENGINE STOPPAGE           WARNING INDICATION                                  TOTAKEOFF        1                      CA       1835 1835                          293447R                     (CAN) AT APPROXIMATLY 300 FEET AGL ON TAKE OFF THE PILOT REDUCED POWER FOR FULL POWER TO CLIMB POWER. A BANG WAS HEARD AND THE ENGINE LOST POWER. THE AIRCRAFT WAS OPERATING ON FLOATS AND WAS LANDED STRAIGHT AHEAD BACK ON TO THE LAKE IT HAD DEPARTED FROM.  INVESTIGATION DETERMINED THAT THE CRANKSHAFT HAD BROKEN BETWEEN CYLINDERS 1-2 /3-4. POSSIBLE CAUSE MAY HAD BEEN MAIN CRANKSHAFT BEARING FAILURE.   THE AIRCRAFT HAD A 50 HR INSPECTION CARRIED OUT 11.1 HRS PRIOR TO THE ENGINE FAILURE. AT THAT TIME THE OIL AND OIL FILTER WERE CHANGED. THE REMOVED OIL FILTER WAS OPENED AND INSPECTED. AT THE TIME OF THE INSPECTION NO METAL OR OTHER CONTAMINANTS WERE DISCOVERED IN THE OIL FILTER. (TC NR 20060920013)                 1H71 3O3  O  A4CE    E5CE    5  CP36EA    
20061011001372006101100137    2006       10         11         CA060921001      420060827G830070BM011030      GEARBOX                                 SNIAS 350   AS350*             EU  TMECA ARRIELARRIEL1B    6OO30NE                              ACCESSORY       DAMAGED         W      B   EMER. DESCENT                                                                                   KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA       5400 1384                                                      (CAN) OIL PRESSURE LINE FITTING AT ACCESSORY GEARBOX (FELL OUT) OF GEARCASE AND SUBSEQUENT COMPLETE LOSS OF OIL IN FLIGHT.  THREADS IN GEARCASE STRIPPED 90 PERCENT; NO PREVIOUS INDICATION OF DISCREPANCY, IE: OIL LEAK OR LOOSENESS. (TC NR 20060921001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3U3  U  H9EU    E19EU                
20061011001382006101100138NM  2006       10         11         CA060921002      120060823G2910AN81510D        UNION                                   DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF23      NE  NR 2 HYD SYST   SHEARED         W      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  APAPPROACH       1                      CA       1300                                                           (CAN) CREW REPORTED NR 2 ENG HYD PUMP CAUTION ILLUMINATED, PRESS AND QTY DEPLETED. FOLLOWING GEAR EXTENSION ON APPROACH. NO EMERGENCY DECLARED. MAINTENANCE FOUND THE HYD FITTING FROM THE EDP TO THE PRESS MANIFOLD SHEARED.  SYD 8-29-002, REPLACEMENT OF ALUMINIUM UNION WITH STEEL UNION COMPLETED. (TC NR 20060921002)                                                                                                                                                                                                                                                                                                                                                                                                                     2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20061213001422006121300142SW  2006       12         13         CA060921003      120060916G6220222011114103    PENDULUM                                BELL  222   222         1182122SW                                                               MAIN ROTOR      SEPARATED       W      A   UNSCHED LANDING                                                                                 E  VIBRATION/BUFFET                                                              CRCRUISE         1                      CA       2006                                                           (CAN) A/C WAS IN CRUISE FLIGHT AT 700 FT, AGL WHEN A SUDDEN VIBRATION BEGAN. THE CREW MADE AN IMMEDIATE LANDING IN A FIELD AND SHUTDOWN. INSPECTION FOUND THAT ONE M/R PENDULUM WEIGHT HAD SEPARATED  AND STRUCK A M/R BLADE. THE DAMAGED AREA IS 3 INCHES LONG BY .1250-.2500 INCH WIDE AND A MAX DEPTH OF 0.0025 INCH. THE DAMAGE BLADE 222-015-500-105 S/N AMR06030 TT4840.7 (TC NR 20060921003)                                                                                                                                                                                                                                                                                                                                           1G72 3U      H9SW                         
20061011001392006101100139NE  2006       10         11         CA060921004      220060911G72503044700         ENGINE                                  BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE  HARTZLHCE4A HCE4A3I     NE                  LEAKING         W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA       148106715                          PS0145                      (CAN) THE CREW REPORTED A LOW OIL PRESSURE INDICATION WHILE TAXING, SOME OIL WAS NOTED ON THE FUSELAGE SO AN AME WAS DISPATCHED. THEY COULD FIND NO AREA OF LEAKAGE DURING INSPECTION AND THE AIRCRAFT WAS REPLENISHED AND NUMEROUS GROUND RUNS DID NOT REVEAL ANYTHING FURTHER. THE AIRCRAFT WAS RETURNING TO A MAINTENANCE BASE WHEN THE AME NOTICED OIL COMING FROM THE BREATHER AREA OF THE ENGINE. THE CREW SHUT THE ENGINE DOWN AND RETURNED TO PLACE OF DEPARTURE WHERE THEY HAD AN UNEVENTFULL LANDING. FURTHER INSPECTION HEARD GRINDING NOISES COMING FROM THE POWER SECTION AREA WHICH INDICATES BEARING DAMAGE IN THAT AREA. THE ENGINE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THE ENGINE HAS BEEN RETURNED TO THE MAIN 2L72 4T4  TRTA24CE   E26NE   5  CP10NE    
20061213001432006121300143CE  2006       12         13         CA060921005      120060919G2697                WIRE                                    BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA  HARTZLHCB3T HCB3TN3     GL  NACELLE         CONTAMINATED    W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CRCRUISE         1                      CA       14827                                                          (CAN) CREW HAD A FIRE WARNING LIGHT COME ON IN FLIGHT, CREW FOLLOWED PROCEDURES AND TURNED THE AIRCRAFT 90 DEGREES TO RULE OUT LIGHT POSSIBLY TRIPPING DETECTORS AND LIGHT REMAINED ON. NO SIGN OF FIRE WAS NOTED VISUALLY ON WING NOR ON THE GLANCE OF INSTRUMENTATION. CREW THEN CARRIED ON AND THE LIGHT WHEN OFF PRIOR TO APPROACH. MAINTENANCE NOTIFIED AND INSPECTED,  FUNCTION CHECKED SYSTEM. SYSTEM FUNCTIONED NORMALLY. WIRING IN NACELLE FOUND  WET DUE TO THE WEATHER CONDITION ENROUTE WHICH WE HAVE DETERMINED A CAUSE FOR AN INTERMITTENT WARNING IN THE PAST. MAINTENANCE SEALED WIRING AS  REQUIRED TO REDUCE THE CHANCE OF THIS HAPPENING WHILE FLYING IN PRECIP. (TC NR 20060921005)                                         1L72 4T4  T  A24CE   E4EA    6  CP15EA    
20061011001402006101100140CE  2006       10         11         CA060921006      120060905G7500                LINE                                    CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE  MCAULY3AF34C3GFR34C703  GL  BLEED AIR       CHAFED          W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA                                                                      (CAN) APPROXIMATELY 10 MIN. INTO THE FLIGHT AT 5500 FT ALTITUDE AND IN CRUISE, THE PILOT NOTICED LIGHT SMOKE COMING FROM THE GENERAL LOCATION OF THE CIRCUIT BREAKER PANEL, AND A DISCOLORING OF THE LT CREW DOOR FWD POST PANEL, LOCATED JUST ABOVE THE CB PANEL. THE PILOT FOLLOWED PROCEDURES FOR CABIN FIRE AND ELECTRICAL FIRE, AND RETURNED SAFELY TO THE AIRPORT OF DEPARTURE. AME`S WERE DISPATCHED TO THE A/C AND UPON INSPECTION FOUND THE CAUSE TO BE THAT THE LT CREW DOOR FWD POST TRIM PANEL WAS TOO CLOSE TO THE BLEED AIR LINE THAT RUNS UP THE DOOR POST FROM THE FIREWALL TO THE WING FOR DE-ICE PURPOSES. THE METAL FLANGE THAT HELD THE PANEL IN PLACE HAD BEEN BENT, POSSIBLY FROM PILOTS REACHING UP AND GRIPPING THE DOOR1H71 3T3  T  A37CE   E4EA    5  CP60GL    
20061213001442006121300144CE  2006       12         13         CA060922001      120060922G324621401400        BEARING         CLEVELAND               BEECH 90    C90A        1152911CE  PWA   PT6   PT6A21      52043EA  HARTZLHCB3T HCB3TN3     GL  RT MAIN GEAR    DESTROYED       W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA       267        DOT6849                                             (CAN) MAINTENANCE NOTICED FLUID LEAKING FROM THE RT MLG BRAKE ASSY. INVESTIGATION REVEALED THAT THE BRAKE ASSY. PISTON RETENTION BOLT WAS THE SOURCE OF THE LEAK. A MORE DETAILED INSPECTION DISCOVERED THAT THE RT MAIN WHEEL INNER WHEEL HALF CONE AND BEARING HAD BEEN DESTROYED. WHEEL REMOVAL SHOWED THAT THE WHEEL ASSY, AXLE, FORWARD AND AFT BRAKE CALIPERS AND LOWER TORQUE LINK HAD BEEN DAMAGED. THE WHEEL DID NOT DEPART THE AIRCRAFT AS THE OUTER WHEEL HALF BEARING ASSY. REMAINED IN TACT AND RETAINED THE WHEEL. ON THE DAY OF DISCOVERY THE AIRCRAFT HAD RECEIVED A PRE-DISPATCH INSPECTION AND FLEW FOR A TOTAL OF 1.8 HOURS AIRTIME AND COMPLETED 5 LANDINGS. THERE WERE NO DEFECTS RECORDED IN THE JOURNEY LOG BOOK POST FLI1L72 3T4  TRT3A20    E4EA    6  CP15EA    
20061213001452006121300145EU  2006       12         13         CA060922002      120060921G6220350A37116200    STOP            SNIAS                   SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1        NE                              MAST YOKE       FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       5739       M4979                                               (CAN) DAILY INSPECTION REVEALED YOKE ASSEMBLY STOP WAS BROKEN BELOW THE ATTACHMENT POINT. THE CABLE CLIP LOWER EDGE WOULD FOLLOW THE CRACK LINE. THE CABLE CLIP WOULD NOT CONTAIN THE BROKEN COMPONENT AND COULD CREATE FURTHER PROBLEMS IF UNIT BECOMES DISLODGED FROM THE RING. THE GRANULAR COMPOSITION OF THE BREAK MAY INDICATE A METALLURGICAL PROBLEM. THIS PART WAS NOT TESTED BUT IS BEING RETAINED IF MORE INVESTIGATION IS REQUIRED. (TC NR 20060922002)                                                                                                                                                                                                                                                                             1G71 3U3  U  H9EU    E19EU                
20061011001412006101100141CE  2006       10         11         CA060925001      120060925G3201264101828       FAIRING                                 CESSNA208   208B        2073701CE  PWA   PT6   PT6A114     52043NE  MCAULY3AF34C3GFR34C703  GL  RT MAIN GEAR    LOOSE           W      O   OTHER                                                                                           D  INFLIGHT SEPARATION                                                           LDLANDING        1                      CA       5509 5509                                                      (CAN) DURING LANDING A SLIGHT THUMP AND A VIBRATION WAS FELT. AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE INSPECTED THE AIRCRAFT AND FOUND THE RT MAIN LANDING GEAR FAIRING (GEAR TO FUSELAGE FAIRING) WAS MISSING THE LOWER PORTION. THIS FAIRING IS A ONE PIECE FAIRING.THE LOWER PORTION OF THE FAIRING HAD BROKEN FREE. FURTHER INSPECTION FOUND MINOR DAMAGE TO THE RT HORIZONTAL STAB. LEADING EDGE. REPAIRS ARE CURRENLY BEEN CARRIED AND A NEW FAIRING ORDERED TO BE REPLACED. (TC NR 20060925001)                                                                                                                                                                                                                                    1H71 3T3  T  A37CE   E4EA    5  CP60GL    
20061011001422006101100142NE  2006       10         11         CA060925002      220060819G7322AKM621RA        CARBURETOR                              DHAV  DHC3  DHC3        2800202EA  WSK   ASZ62 ASZ62IRM18       NE                              ENGINE          LEAKING         W      A   UNSCHED LANDING                                                                                 RE PARTIAL RPM/PWR LOSS      VIBRATION/BUFFET                                    CRCRUISE         1                      CA       311                                                            (CAN) ACCORDING TO THE PILOT WHILE IN FLT THE ENGINE STARTED TO RUN ROUGH AND SPUTTERED A FEW TIMES, THE PILOT CHECKED LT AND RT MAGNETOS, CARB HEAT, BOOST PUMP, GAUGES-OIL TEMPERATURE AND PRESSURE, FUEL PRESSURE AND CYLINDER HEAD TEMPERATURE. ALL GAUGES WERE INDICATING NORMAL RANGES. SWITCHED FUEL TANKS AND THE PROBLEM THEN WENT AWAY. A FEW MINUTES LATER THE PROBLEM OCCURRED AGAIN. THE PILOT THEN NOTIFIED A COMPANY AIRCRAFT AND PROCEEDED WITH UNSCHEDULED LANDING FOR PURPOSE OF INVESTIGATING PROBLEM. THE ENGINE PROBLEM WAS NOT EVIDENT ON THE APPROACH AND LANDING. ONCE ON THE WATER THE PILOT THEN WENT TO SHORE AND DRAINED THE FUEL SUMPS AND CHECKED THE CARB HEAT FUNCTION. THE PILOT THEN DID MULTIPLE RUN UPS AT D1H71 3R3  R  A815    E10NE                
20061213001462006121300146SO  2006       12         13         CA060925003      120060830G27976345703         CONNECTOR       PIPER                   PIPER PA28  PA28180     7102808SO  LYC   O360  O360A4A     41514EA  SNSNCH76E   76EM8S5     EA  RUDER TRIM ARM  BROKEN          W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             CLCLIMB          1                      CA       3676                                                           (CAN) WHEN MANUAL RUDDER TRIM WAS APPLIED THE RUDDER FAILED TO RESPOND. SUBSEQUENT INSPECTION FOUND THAT THE ARM THAT CONNECTS THE TRIM ACTUATOR TO THE RUDDER CONTROL ASSEMBLY HAD BROKEN OFF THE ASSEMBLY AT THE EDGE OF THE WELD. THE COMPLETE RUDDER TRIM ARM ASSEMBLY WAS REMOVED AND REPLACED WITH A NEW UNIT. METAL FATIGUE IS SUSPECTED. (TC NR 20060925003)                                                                                                                                                                                                                                                                                                                                                                            1L71 3O3  O  2A13    E286    5  NP4EA     
20061011001552006101100155NE  2006       10         11         CA060925004      220060912G852027056CAI        PISTON                                  DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985*       52008NE  HAMSTD2D    2D30        NE  ENGINE          CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA            946                                                       (CAN) DURING REGULAR INSPECTION LOW COMPRESSION WAS NOTED ON NR 1 CYL. CYLINDER WAS REMOVED AND PISTON WAS CRACKED. CYLINDER ASSY WAS REPLACED. AIRCRAFT GROUND RUN WAS CARRIED OUT SATISFACTORY. (TC NR 20060925004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1H71 3R3  RRCA806    5E1     5  CP206     
20061213001122006121300112EA  2006       12         13         CA060925005      120060922G7931                SCREEN                                  CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30015NE                              OIL SCAVENGE    FAILED          W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) ABOUT 50 NM EAST AND AT FL330 THE CREW REPORTED LT ENG OIL PRESSURE WARNING LIGHT WITH FLUCTUATING LOW OIL PRESSURE READINGS (20-46PSI) AT IDLE POWER LT OIL TEMP WAS INCREASING. THE CREW ELECTED TO SHUT DOWN THE LT ENGINE.  LINE MAINTENANCE REMOVED LT ENGINE OIL PUMP AND INSPECTED ALL SCAVENGE SCREENS IAW SB 79-001200 OIL. FOUND SCAVENGE SCREEN PLUGGED WITH COKED OIL. REPLACED OIL PUMP AND PUMP SCREENS IAW AMM 79-21-01 ENGINE RUNS CARRIED OUT AND THE AIRCRAFT WAS RELEASED INTO SERVICE. THE OIL FILTER AND SAMPLE HAVE BEEN SENT FOR ANALYSIS. (TC NR 20060925005)                                                                                                                                                     2L72 4F4  FRTA21EA   E15NE                
20061208000062006120800006SW  2006       12         8          CA060925007      120060923G2435                SHAFT                                   BELL  206   206B        1181511SW  ALLSN 250C  250C20B     03013GL                              STARTER GEN     SHEARED         W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA            461                                                       (CAN) PILOT REPORTED THAT THE STARTER WOULD NOT TURN THE ENGINE, IT WOULD JUST SPIN.  MAINTENANCE FOUND THAT THE SHAFT ON THE STARTER HAD BEEN SHEARED. STARTER HAD BEEN REPLACED AND AIRCRAFT RETURN TO SERVICE. (TC NR 20060925007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1G71 3U3  U  H2SW    E4CE                 
20061011001602006101100160CE  2006       10         11         CA060925008      120060919G321345325400018     STRUT                                   LEAR  45    45LEAR      5170805CE  GARRTTTFE731TFE7312     01518WP                              NLG             UNDERSERVICED   W      A   UNSCHED LANDING                                                                                 WJ INADEQUATE Q C            WARNING INDICATION                                  CLCLIMB          1                      CA       2707                                                           (CAN) AFTER TAKEOFF LANDING GEAR WAS SELECTED UP AND ALL LANDING GEAR NOT-UP AND LOCKED LIGHTS DID NOT EXTINGUISH. AIRCRAFT DIVERTED AND AFTER LANDING IT WAS DISCOVERED THE NOSE STRUT WAS COMPLETELY COLLAPSED. THE NOSE STRUT WAS RE-SERVICED WITH NITROGEN AND GEAR SWINGS ACCOMPLISHED WITH NO PROBLEMS. ON RETURN TO OUR BASE, THE NOSE STRUT WAS MODIFIED TO NEW PN 4532230001-804 (MODIFICATION OF UPPER STRUT SEAL ASSY. INSTALLATION) (TC NR 20060925008)                                                                                                                                                                                                                                                                             2L72 4F4  FRTT00008WIE6WE                 
20061011001612006101100161NM  2006       10         11         CA060925009      120060923G3297D4668           CONNECTOR                               BOEING727   727223      1384074NM  PWA   JT8   JT8D15      52051NE                              ANTI-SKID SYS   FAULTED         W      O   OTHER                                                                                           O  OTHER                                                                         LDLANDING        1                      CA                                                                      (CAN) ON LANDING, THE NR 1 AND NR 4 TIRES SKIDDED UNTIL THEY BLEW OUT. THE A/C HAD TO BE TOWED FROM THE RUNWAY. AVIONICS PERSONELL DISCOVERED AN INTERMITTENT FAULT IN AN ANTI-SKID CONNECTOR (D4668) ABOVE THE RT GEAR LEG. ALL 4 TIRES AND THE CONNECTOR WERE REPLACED AND THE A/C RETURNED TO SERVICE. (TC NR 20060925009)                                                                                                                                                                                                                                                                                                                                                                                                                   2L73 4F4  F  A3WE    E2EA                 
20061208000072006120800007CE  2006       12         8          CA060926003      120060921G561010138402524     WINDSHIELD                              BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA  HARTZLHCB3T HCB3TN3     GL  COCKPIT         CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA       1354                                                           (CAN) IN HOLDING PATTERN  AT 9,000 FT/-2C/WINDSHIELD HEAT ON LOW; OUTER PANE OF WINDSHIELD CRACKED FOR NO APPARENT REASON. FLIGHT CONTINUED  AND LANDED WITHOUT INCIDENT.  NO EVIDENCE OF BIRD STRIKE OR FOREIGN OBJECT DAMAGE NOTED.  (TC NR 20060926003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L72 4T4  T  A24CE   E4EA    6  CP15EA    
20070507000932007050700093CE  2007       5          7          CA060926004      120060923G273111452403725     CONTROL CABLE                           BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE  HARTZLHCE4A HCE4A3I     NE  ELEVATOR TRIM   BROKEN          W      O   OTHER                                                                                           O  OTHER                                                                         APAPPROACH       1                      CA       22576                                                          (CAN) CREW REPORTED DIFFICULTY WITH CHANGING THE ELEVATOR TRIM ON APPROACH.  MAINTENANCE FOUND THAT THE ELEVATOR TRIM CABLE HAS BROKEN AT THE TRIM SERVO/CAPSTAN LOCATION. THIS SERVO/CAPSTAN COMPONENT IS ONLY INSTALLED ON AUTOPILOT EQUIPPED 1900D`S OF WHICH THERE ONLY VERY FEW. THE CAPSTAN REQUIRES ROUTING OF THE .0625 CABLE. (TC NR 20060926004)                                                                                                                                                                                                                                                                                                                                                                                      2L72 4T4  TRTA24CE   E26NE   5  CP10NE    
20061011001622006101100162GL  2006       10         11         CA060926005      320060913G6111M10876ANS       BLADE           HARTZL                  STBROSSD3   SD360       8100606EU  PWA   PT6   PT6A65AR    52043NE  HARTZLHCB5M HCB5MP3     GL  PROPELLER       CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            3341  EVA2469                             EVA2469         (CAN) UPON VISUAL INSPECTION , CORROSION WAS FOUND ON THE BLADE SHANK. AFTER REWORK TO MINIMUM DIMENSION DAMAGE STILL REMAINS. BLADE WIDTH AND THICKNESS IS WELL ABOVE MINIMUM DIMENSION. ALL 5 BLADES ARE U/S.  (TC NR 20060926005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2H72 4T4  T  A41EU   E4EA    6  CP44GL    
20061011001632006101100163GL  2006       10         11         CA060927001      220060919G723023053990        SCROLL          RROYCE                  BELL  206   206L1       1182107SW  ALLSN 250C  250C30P     03013GL                              COMPRESSOR      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       6362 5265  CAC90168                                            (CAN) DURING SCHEDULED 100/300 HR INSPECTION COMPRESSOR SCROLL FOUND CRACKED ON VISUAL INSPECTION. A/C GROUNDED AND COMPRESSOR REPLACED. RECOMMEND BETTER DAILY INSPECTIONS BEFORE FIRST FLIGHT. (TC NR 20060927001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1G71 3U3  U  H2SW    E1GL                 
20061208000202006120800020SW  2006       12         8          CA060927003      120060927G5730                SKIN                                    SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE33111U   01514WP  MCAULY4HFR344HFR34C652  NE  WINS            CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       28657                                                          (CAN) PERIMETER WAS INFORMED FROM ANOTHER OPERATOR OF THE SAME AIRCRAFT OF POTENTIAL WING SKIN CRACKS EMINATING FROM THE LT AND RT BATTERY VENT SCOOPS INSTALLED IN THE LOWER WING SKIN BETWEEN THE NACELLE AND FUSELAGE. INITIAL VISUAL INSPECTION REVEALED NO CRACKS BUT WITH THE USE OF EDDY CURRENT THE CRACKS WERE DISCOVERED AND FOUND PROGRESSING FROM 3 OF THE 4 CORNERS OF THE BATTERY VENT SCOOP AT THE WING SKIN. THE 4 AC OF THIS TYPE INSPECTED, 3 HAD CRACKS FOUND ON THE LOWER WING BATTERY VENT SCOOPS. THEY WERE INSPECTED AND ALL FOUND WITH EDDY CURRENT INSPECTION METHOD. REPAIR DESIGN CERTIFICATE RDC C-RA06-235/D HAS BEEN APPROVED FOR THE REPAIR OF THIS DEFECT. (TC NR 20060927003)                                  2L72 4T4  TRTA8SW    E4WE    6  C3PNE     
20061011001642006101100164NM  2006       10         11         CA060928001      120060928G7312S2L354          O-RING                                  DHAV  DHC8  DHC8301     1386003NM                                                               FUEL HEATER     DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING THE ACCOMPLISHMENT OF THE TASK 2150/05 (HEAT EXCHANGER CORE CLEANNING) WE FOUND A NEW O-RING DAMAGED IN THE ORIGINAL PACKAGE. THE O-RING COME FROM NATIONNAL O-RING  MFGR. COMPD. NR V-14  MFG BATCH NR: 58978  CURE DATE: 4088  EXP. DATE: OCT 01,2009 THE O-RING WAS DAMAGE ALL AROUND. A OTHER O-RING WITH THE SAME BATCH AND PN USE ON THE SAME JOB WAS FOUND OK FOR THE INSTALLATION. (TC NR 20060928001)                                                                                                                                                                                                                                                                                                                     2H72 4T    RTA13NM                        
20061011001652006101100165NE  2006       10         11         CA060928002      220060916G7200                ENGINE                                  AIRBUS320   A320211     3930320EU  GE    CFM56 CFM565A     13802NE                              NR 2            VIBRATION       W      C   ABORTED TAKEOFF                                                                                 E  VIBRATION/BUFFET                                                              TOTAKEOFF        1                      CA                                          731250                      (CAN) T/O REJECTED AT APPROX 110 KTS DUE SERIOUS VIBRATIONS (SUSPECT RT MAIN GEAR).  AUTO BRAKE USED MAX BRAKE TEMP IND 480 DEG FOR NR 2, OTHERS WERE 450-480. ON STARTING NR 2 ENGINE, FELT HIGH VIBRATION AND HIGH EGT, ABORTED ENGINE START. WHEN TURNING NR 2 FAN BY HAND, COULD HEAR N2 TURNING AS WELL. FOUND RT GEAR FIXED DOOR ASSY WITH 2 ATTACH STUDS SHEARED.  SB A320-52-1100 ALREADY AVAILABLE TO INSTALL IMPROVED ATTACH STUDS.                                                                                                                                                                                                                                                                                                   2L72 4F4  FRTA28NM   E29NE                
20070507000942007050700094SW  2007       5          7          CA060928003      120060909G5521222182          STRINGER                                BBAVIA7     7ECA        21101NNSW  LYC   O235  O235K2C     41505EA  SNSNCH72C   72CK        EA  FUSELAGE        FAILED          W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      CA       3626                                                           (CAN) AFTER RECOVERING FROM AN AEROBATIC MANEUVER, THE PILOT FOUND THAT FULL DOWN ELEVATOR TRAVEL COULD NOT BE OBTAINED. A UNEVENTFUL RETURN TO THE AIRPORT AND LANDING WAS CARRIED OUT.  ONCE THE ELEVATOR BELLCRANK COVER WAS REMOVED, THE LT GUSSET FROM THE AFT STRINGER SUPPORT FELL OUT AND FULL ELEVATOR TRAVEL WAS OBTAINED. EXAMINATION OF THE GUSSET, SUPPORT AND RIVETS INDICATED THAT VIBRATION OF THE FABRIC IN FLIGHT HAD LOOSENED THE SOFT ALUMINUM POP RIVETS THAT THE MFG HAD USED IN ATTACHING THE GUSSET HAD WORKED LOOSE AND EVENTUALLY BROKEN, ALLOWING THE GUSSET TO FALL INTO THE BELLY AND WORK ITS WAY BACK INTO THE TAIL WHERE IT BECAME LODGED IN THE NARROW CLEARANCES AROUND THE ELEVATOR BELLCRANK.  THE SUBMITTER1H71 3O3  O  A759    E223    5  NP9045    
20061208000212006120800021CE  2006       12         8          CA060928004      120060817G32101158100325      TORQUE KNEE                             BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA  HARTZLHCD4N3HCD4N3A     GL  MLG             CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A ROUTINE INSPECTION THE LT UPPER TORQUE KNEE WAS FOUND CRACKED. THE TORQUE KNEE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. SEE ATTACHED PICTURES. (TC NR 20060928004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L72 4T4  T  A24CE   E4EA    5  CSTC      
20061211001542006121100154GL  2006       12         11         CA060928005      320060925G6111R1015255        BLADE                                   DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE  HARTZLHCB3R HCB3R302    GL  PROPELLER       DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2015                                           AH4             (CAN) PROPELLER RECEIVED FOR O/H. UPON DISMANTLING DISCOLORATION ON THE BLADE SHANKS WAS NOTED. SHANKS WERE LIGHTLY MEDIA BLASTED AND THE DAMAGE IS MORE SEVERE THAN AT FIRST INSPECTION. BLADE SHANK RADIUS IS AT 4.194 INCHES MINIMUM FOR REPAIR IS 4.187 INCHES. THESE 3 BLADES ARE UNSERVICEABLE DUE TO THIS CORROSION. (TC NR 20060928005)                                                                                                                                                                                                                                                                                                                                                                                                 1H71 3R3  RRCA806    5E1     5  CP28EA    
20061208000222006120800022GL  2006       12         8          CA060928006      320060915G6114C3054           FERRULE         MCAULY                  CESSNA185   185         2072802CE  CONT  O470  IO470F      17026SO  MCAULY2A34C D2A34C58    GL  PROPELLER       CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            69    778082                                              (CAN) PROP RECEIVED FOR 10 YR. O/H. UPON DISMANTLING DISCOVERED CORROSION DAMAGE TO FERRULE. PART IS U/S (TC NR 20060928006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H71 3O3  ONC3A24    3E1     5  CP3EA     
20061011001662006101100166EA  2006       10         11         CA060929001      120060918G5751DSC5108         BEARING                                 DHAV  DHC8  DHC8311     1386006EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF15      NE  LT AILERON      WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) THE DEFECT WAS FOUND DURING A REPAIR OF WING TIP LIGHTNING STRIKE ON SEPTEMBER 18, 2006 AT A/C TCSN 35,548 CYCLES. AT THE OUTER AILERON THE HINGE FITTING ASSY SHOWED A PREMATURE BEARING WEAR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20061011001672006101100167NM  2006       10         11         CA060929002      120060926G278110608197        INDICATOR                               BOEING727   727233      138408ANM  PWA   JT8   JT8D15      52051NE                              KRUEGER FLAPS   FAILED          W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      CA                                                                      (CAN) DEPARTING THE CREW OBSERVED A L/E FLAP UNRETRACTED INDICATION AT THE NR 1 POSITION.THE AIRCRAFT RETURNED TO POINT WITHOUT FURTHER INCIDENT. MAINTENANCE FOUND THE POSITION INDICATION SWITCH HAD FAIL AT THE NR 1 KRUEGER FLAP LOCATION. THE SWITCH WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20060929002)                                                                                                                                                                                                                                                                                                                                                                                                                2L73 4F4  FRTA3WE    E2EA                 
20070104000012007010400001    2007       1          4          CA060929003      420060920G6122941521          SCREW                                   AMBLP A150  A150        3850110NM  ROTAX 914   ROTAX914         EU                              GEARBOX         BROKEN          W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             NRNOT REPORTED   1                      CA       2077 577                                                       (CAN) PROP WOULD NOT CHANGE PITCH DURING RUN-UP. GEARBOX WAS REMOVED AND THE SCREW HOLDING THE GOVENOR DRIVE COUPLING TO THE DRIVE GEAR WAS FOUND BROKEN. THE SCREW APPEARED TO HAVE FAILED FROM TORQUE OVERLOAD. THE SCREW, DRIVE COUPLING AND GEAR WERE REPLACED AND ENGINE RETURNED TO SERVICE. NO FOD NOTED. THE ENGINE HAS 577 HRS SINCE OVERHAUL. (TC NR 20060929003)                                                                                                                                                                                                                                                                                                                                                                     1B72 3O3  O0 SOOOO2SEEXPE3I               
20061208000292006120800029EU  2006       12         8          CA060929004      120060928G324650104882A       WHEEL                                   SAAB  SF340 340B        7860101EU  GE    CT7TP CT79B       30030NE  ROTOL R390  R3904123F27 NE  MLG             MISSING         W      O   OTHER                                                                                           D  INFLIGHT SEPARATION                                                           TXTAXI/GRND HDL  1                      CA                                                                      (CAN) AFTER ARRIVAL, THE CAPTAIN WAS NOTIFIED THAT THE AIRCRAFT NR 3 MAINWHEEL WAS MISSING.  MAINTENANCE INSPECTION REVEALED THAT ALTHOUGH THE WHEEL NUT AND LOCKING BOLT WERE IN PLACE THE WHEEL ITSELF WAS MISSING. (TC NR 20060929004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4T4  TRTA52EU   E8NE    6  CP31NE    
20061208000302006120800030EA  2006       12         8          CA060929005      220060928G7313310926302       DUCT                                                                       PWA   PT6   PT6A34      52043EA                              ENGINE          DAMAGED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       3035                               RB0207                      (CAN) WHILE PERFORMING A BOROSCOPE INSPECTION DURING A REGULARLY SCHEDULED FUEL NOZZLE CHANGE, DAMAGE WAS FOUND ON THE LARGE EXIT DUCT.  THE (LED) WAS CHANGED AND UPON CLOSER INSPECTION IT WAS FOUND THAT A LARGE HOLE HAD BEEN BURNED THROUGH ONE LAYER OF THE DUCT AND CRACKS HAD FORMED IN THE SECOND LAYER.  THE ENGINE HAD  OF 3034.6 TSN HOURS AND 6819 CYCLES.  THIS WAS THE THIRD (LED) THAT THIS OPERATOR HAS HAD PROBLEMS WITH.  IT IS SUSPECTED THAT EITHER A BAD FUEL NOZZLE (NOZZLES HAVE BEEN SENT OUT FOR TESTING) OR MATERIAL DEFECT CAUSED THE FAILURE. (TC NR 20060929005)                                                                                                                                                         4  T          E4EA                 
20061208000312006120800031NE  2006       12         8          CA061002001      220061002G7200AS21040         BOLT                                    GULSTMG1159 GIV         3980115SO  RROYCETAY   TAYMK6118        NE                              ENGINE          WRONG PART      W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       7000                               16230                       (CAN) NON APPROVED AS21040 BOLT WAS FOUND. BOLT HEAD WAS MACHINED TO ADD PN AS21040.  BOLT END ALSO MACHINED WITH A CENTER HOLE, THREAD LENGTH SHORTER AND DIAMETER OF BOLT IS UNDERSIZE. BOLT LOCATIONS ON ENGINE; CLIPPING POINT FOR P3 AIR TUBE TO FFR UNION P3 LIMITER,  IP BLEED VALVE CLAMPING SEAL/RETAINING SEAL AND LP FUEL FILTER MOUNTING BOLT.  (TC NR 20061002001)                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA12EA   A25NE                
20061208000502006120800050NE  2006       12         8          CA061002002      220060909G72003066T90G02      ENGINE                                  SKRSKYS92   S92A               NE  GE    CT7TP CT79B       30030NE                              NR 1            FAILED          W      A   UNSCHED LANDING                                                                                 XJ ENGINE FLAMEOUT           WARNING INDICATION                                  APAPPROACH       1                      CA                                                                      (CAN) THE FOLLOWING REPORT REFERS TO FLT OCCURRENCE REPORT NR 06-00894. THE AIRCRAFT WAS OPERATING FOR CUSTOMER ON AN OFFSHORE FLIGHT. AT APPROX 09.58 WHILE ON SHORT FINAL APPROACH (IN VMC), 2 POPS WERE HEARD BY THE CREW. A MISSED APPROACH WAS INITIATED, AND DURING THE CLIMB OUT IT WAS APPARENT THE NR 1 ENGINE HAD HIGH TGT AND LOWER TORQUE THAN THE NR 2 ENGINE. DURING THE CLIMB SEVERAL MORE POPS WERE HEARD. AFTER REACHING A SAFE HEIGHT, THE EMERGENCY CHECKLIST WAS FOLLOWED FOR (COMPRESSOR STALLING) ON THE NR 1 ENGINE.  IAW THE CHECKLIST, THE NR 1 ENGINE WAS BROUGHT BACK TO IDLE, AND THE COMPRESSOR STALLING CEASED. THE CREW THEN ELECTED TO RETURN TO DEPARTURE, WITH NR 1 ENGINE AT IDLE, IAW THE EMERGENCY CHECKLIS2G72 4U4  T  R00024BOE8NE                 
20061208000512006120800051    2006       12         8          CA061002003      420060824G3442                DIODE           HONEYWELL               DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF15      NE  WX RADAR SYSTEM BURNED          W      G   O2 MASK DEPLOYED                                                                                B  SMOKE/FUMES/ODORS/SPARKS                                                      DEDESCENT        1                      CA       2678926789 1643                                                (CAN) ON DECENT THROUGH 10,000 FEET, F/O NOTICED A HAZY SMOKE IN THE COCKPIT. BOTH THE CAPTAIN AND THE F/O BEGAN TO FEEL A BURNING SENSATION IN THEIR THROATS. THEY DONNED THEIR OXYGEN MASKS AND REQUESTED A VISUAL DIRECT APPROACH.  THERE WAS A DEFINITE ELECTRICAL SMELL IN THE COCKPIT. THE CABIN HAD A SLIGHT ODOR BUT NOT RECOGNIZABLE. PASSENGERS WERE UNAWARE OF THE SITUATION, NO PASSENGER REACTION. CREW DID NOT DECLARE AN EMERGENCY AND LANDED SAFELY WITHOUT FURTHER INCIDENT. MAINTENANCE DISCOVERED WEATHER RADAR INDICATOR TO BE AT FAULT. WEATHER RADAR INDICATOR AND TRANSMITTER/RECEIVER REPLACED AND TESTED SERVICEABLE. AIRCRAFT SUCCESSFULLY TEST FLOWN PRIOR TO RETURN TO SERVICE. INDICATOR HAD 865:02 HOURS AND 830 L2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20061208000522006120800052WP  2006       12         8          CA061002004      120060805G5411C04618          FRAME                                   ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              NACELLE         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       350  350                                                       (CAN) AFT TAB WAS FOUND TO BE CRACKED UPON ROUTINE SCHEDULED INSPECTION. NEW FRAME ORDERED AND HELICOPTER WAS NOTIFIED OF THE PROBLEM.  THEY HAVE SINCE RELEASED A NEW BULLETIN ADDING A CLAMP TO THE FRAME.  THIS AIRCRAFT IS REGISTERED WITH MFG FOR WHEN THE CORRECTIVE PARTS BECOME AVAILABLE. (TC NR 20061002004)                                                                                                                                                                                                                                                                                                                                                                                                                          1G71 3O3  O  H11NM   1E4                  
20061208000532006120800053SW  2006       12         8          CA061002005      120060831G2711                CABLE                                   BBAVIA7     7GCBC       1220601SW  LYC   O320  O320A2B     41508EA  MCAULY1A175 1A175GMA    GL  AILERON TAB     DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       48                                                             (CAN) IAW AD 2005-24-10 AND MFG SERVICE LETTER NR 427, THE FLIGHT CONTROL CABLE INCLUDED IN THE WING RETROFIT KIT WAS INSPECTED FOR PROPER SWAGING. AILERON CABLES REQUIRED PROPER SWAGING.  (TC NR 20061002005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1H71 3O3  ONCA759    E274    5  NP857     
20061208000542006120800054SO  2006       12         8          CA061002006      120060928G3230                LANDING GEAR                            PIPER PA31  PA31P       7103120SO  LYC   O541  TIGO541E1A  41539EA  HARTZLHCC3Y HCC3YN      GL  RIGHT           FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) DEFECT: UNABLE TO PUT DOWN GEAR AND GET 3 GREEN LIGHTS. UPON 4TH TRY WHILE IN A HARD RT TURN, FINALLY GOT RT MAIN GEAR DOWN AND LOCKED. AIRCRAFT RETURNED TO BASE WITH LANDING GEAR IN DOWN/LOCKED POSITION UNDER FERRY FLIGHT PERMIT.  RECTIFICATION: LANDING GEAR INSPECTED, SYSTEM FLUSHED AND BLED IAW MFG MM. LANDING SWUNG 50 FAULT FREE TIMES. UNABLE TO DUPLICATE FAULT. AIRCRAFT RETURNED TO SERVICE.  (TC NR 20061002006)                                                                                                                                                                                                                                                                                                       1L72 3O3  O  A8EA    E19EA   5  CP25EA    
20061208000552006120800055EA  2006       12         8          CA061002007      220060928G732125245019        FUEL CONTROL                            PIPER PA31  PA31P       7103120SO  LYC   O541  TIGO541E1A  41539EA  HARTZLHCC3Y HCC3YN      GL  ENGINE          FAILED          W      O   OTHER                                                                                           RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  NRNOT REPORTED   1                      CA                                                                      (CAN) UNCONTROLLABLE POWER FLUCTUATIONS AT HIGH POWER SETTINGS ON LT ENGINE.  FOUND FUEL CONTROL UNIT P/N 2524501-9 S/N 70084801 TO BE UNSERVICEABLE. REPLACED WITH REBUILT UNIT P/N 2524501-9 S/N 70157810. SYSTEM GROUND RUN SERVICEABLE. (TC NR 20061002007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L72 3O3  O  A8EA    E19EA   5  CP25EA    
20061208000662006120800066WP  2006       12         8          CA061002009      120060926G67971520            WIRE            ROBSIN      C0581       ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              CYCLIC GRIP     CHAFED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2196                                                           (CAN) GRIP ASSEMBLY OPENED TO INSTALL CARGO HOOK SWITCH AND FOUND STARTER BUTTON WIRE CHAFED UP AGAINST A GRIP MOUNTING SCREW.  THE INSULATION WAS SPLIT OPEN 0.25 INCH AND 2 WIRE STRANDS REMAINED UNBROKEN. (TC NR 20061002009)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1G71 3O3  O  H11NM   1E4                  
20061208000672006120800067EU  2006       12         8          CA061002010      120060928G2497E0052R22B55SNE  CONNECTOR                               AEROSPATR42 ATR42300    8680920EU  PWA   120   PW120            NE  HAMSTD14SF  14SF5       NE  ELECTRICAL PWR  BURNED          W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      LDLANDING        1                      CA                                                                      (CAN) CONNECTOR WAS SHORTING ACROSS INSULATING MATERIAL. PROBLEM WAS BETWEEN ADJACENT PIN CONTACTS. MATING CONNECTOR 704VC WAS UNHARMED. BURNED CONTACTS HAD LOTS OF BLACK CARBON ON THEM. (TC NR 20061002010)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2H72 4T4  TRTA53EU   E20NE   6  CP7NE     
20061208000692006120800069GL  2006       12         8          CA061002011      320060929G61975038912131      CONNECTOR                               BEECH 1900  1900C       1154161CE  PWA   PT6   PT6A65B     52043EA  HARTZLHCB4M HCB4MP3     GL  NR 2 PROPELLER  DAMAGED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) FAULT - LT SIDE AUTOFEATHER LIGHT DOES NOT ARM.   NR 2 HIGH PRESS FEATHER SWITCH CONNECTOR, CONNECTOR PIN LETTER B REPLACED. SWITCH CONNECTORS CLEANED. PROBLEM SEEMED TO BE CAUSED BY CONTAMINATION. (TC NR 20061002011)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4T4  TRTA24CE   E4EA    6  CP56GL    
20061208000702006120800070EU  2006       12         8          CA061003001      120060924G3240AC13794         PRESSURE VALVE                          BRAERO748   HS7482A     4231001EU  RROYCEDART  DART5342         EU  ROTOL R4304 R2124304    EU  BRAKE           MALFUNCTIONED   W      D   RETURN TO BLOCK                                                                                 J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      CA            11340                                                     (CAN) DURING TAXI TO POSITION THE THE MAIN HYDRAULIC SYSTEM WAS CYCLING EVERY 30 SECONDS. THE CREW RETURNED TO COMPANY RAMP. THE IB BRAKE PRESSURE REDUCING VALVE WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20061003001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 3T4  T  A24EU   A196    6  CP899     
20061208000712006120800071EU  2006       12         8          CA061003003      120060928G3060                BRUSH BLOCK                             AEROSPATR42 ATR42300    8680920EU  PWA   120   PW120            NE  HAMSTD14SF  14SF5       NE  PROPELLER       UNKNOWN         W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB AFTER DEPARTURE THE CREW OBSERVED AN ANTI-ICE FAULT ON NR 1 POSITION.  THE AIRCRAFT RETURNED TO POINT OF DEPARTURE. MAINTENANCE REPLACED THE BRUSHES ON NR 1 BRUSH BLOCK AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20061003003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2H72 4T4  TRTA53EU   E20NE   6  CP7NE     
20061208000722006120800072CE  2006       12         8          CA061003004      120060926G5740114430002179    ANGLE                                   BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE  HARTZLHCE4A HCE4A3I     NE  BS 288          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       9184                                                           (CAN) WHILE COMPLETING A PRESSURIZATION CHECK OF THE CABIN, AIR WAS FOUND TO BE LEAKING OUT AROUND SPAR/ FUSE JOINT AREA. CRACKS WERE FOUND ON THE LT AND RT WING-FUSELAGE CLOSING ANGLES AT FS 288  IN THE SAME SPOTS MEASURING 1.7500 INCHES EACH.  LT ANGLE IS P/N 114-430002-179 AND THE RT IS114-430002-180.  CRACKS REPAIRED IAW SRM 53-90-23. (TC NR 20061003004)                                                                                                                                                                                                                                                                                                                                                                        2L72 4T4  TRTA24CE   E26NE   5  CP10NE    
20061208000732006120800073GL  2006       12         8          CA061003005      120061001G2910                HYDRAULIC SYSTEM                        BOMBDRBD100 BD1001A10   1390044GL                                                               NR 2            LEAKING         W      E   ENGINE SHUTDOWN                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA                                                                      (CAN) WHILE VERIFYING A NOSE WHEEL STEERING SNAG DURING TAXI TEST, A LOSS OF HYDRAULIC FLUID FROM NR 2 SYSTEM OCCURED.  LT AND RT ENGINES WERE SHUTDOWN AND AREA WAS INSPECTED.  HYDRAULIC FLUID WAS FOUND TO HAVE SPRAYED IN AFT FUSELAGE AND ON THE RT SIDE. (TC NR 20061003005)                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F    RTT00005NY                     
20061208000742006120800074SO  2006       12         8          CA061004001      220060924G731464936849A1      PUMP                                    DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO  SNSNCHW69EK W69EK63     EA  ENGINE          OUT OF ADJUST   W      O   OTHER                                                                                           Y  ENGINE STOPPAGE                                                               DEDESCENT        1                      CA       88                                 650201                      (CAN) AIRCRAFT ENGINE FAILED IMMEDIATELY AFTER SPIN RECOVERY.  INSTRUCTOR CONFIRMED FUEL PUMP ON AND MIXTURE FULL RICH.  INSTRUCTOR ESTABLISHED BEST GLIDE ATTITUDE AND RESTARTED ENGINE IAW AFM (ENGAGING STARTER).  UPON LANDING AND TAXI, INSTRUCTOR KEPT POWER ABOVE 1000 RPM, SO THERE IS NO FURTHER INFO ON LOW POWER BEHAVIOR DURING THIS FLIGHT.  IMMEDIATELY PUT TEST GAUGES ON, AND RAN UP AIRCRAFT.  UNMETERED PRESSURE WAS APPROXIMATELY 1.6 PSI LOW AND METERED PRESSURE WAS APPROX 2 PSI LOW.  IDLE MIXTURE RISE OF 10 TO 20 RPM.  IT IS WORTH NOTING THAT I FELT THE ENGINE DID NOT (SOUND) AS IF IT WAS FUNCTIONING PROPERLY.  WE HAVE CURRENTLY REMOVED ALL FUEL SCREENS, INSPECTED AND CLEANED.  MODERATE CONTAMINATION FOUND 1L71 3O3  ONTTA4CH   E7SO    5  NTA4CH    
20061208000762006120800076NM  2006       12         8          CA061004003      120061002G323365446604        ACTUATOR                                BOEING737   737242C     1384478NM  PWA   JT8   JT8D9A      52048NE                              NLG             BYPASSING       W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) ON CLIMB OUT THE NOSE LANDING GEAR FAILED TO RETRACT. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT INCIDENT. MAINTENANCE DETERMINED THAT THE NOSE LANDING GEAR GRAVEL DEFLECTOR ACTUATOR HAD FAILED. THE ACTUATOR WAS REPLACED AND THE AIRCEAFT WAS RETURNED TO SERVICE. (TC NR 20061004003)                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F4  F  A16WE   E2EA                 
20061208000782006120800078EA  2006       12         8          CA061004004      120061002G272282960010147     TUBE                                    DHAV  DHC8  DHC8311     1386006EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF15      NE  RUDDER ACTUATOR CRACKED         W      K   NONE                                                                                            KJ FLUID LOSS                WARNING INDICATION                                  ININSP/MAINT     1                      CA                                                                      (CAN) CREW NOTICED FLUID STAINS AND ACCUMULATION ON RT SIDE OF RUDDER AND TAIL CONE.  MAINTENANCE FOUND CRACK AT FIRST ELBOW FROM TOP FITTING OF  NO. 1 HYDRAULIC SYSTEM PRESSURE LINE TO THE RUDDER ACTUATOR. LINE REPLACED AND SYSTEM LEAK CHECKED SERVICEABLE. IPC REF CH 27-21-00 FIG. 20 ITEM 120. AFTT 34,145:10 HOURS, AFTC 38202. (TC NR 20061004004)                                                                                                                                                                                                                                                                                                                                                                                   2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20061208000792006120800079EU  2006       12         8          CA061004005      120060926G3250114068003       ACTUATOR                                PIAGIOP180  P180        6960204EU  PWA   PT6   PT6A66      52043NE  HARTZLHCE5N HCE5N3      GL  NLG STEERING    FAILED          W      D   RETURN TO BLOCK                                                                                 J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      CA       136  136                                                       (CAN) PILOTS REPORTED NOSE GEAR STEERING FAILURE.  NOSE GEAR ACTUATOR REPLACED.  SYSTEM TESTED AND AIRCRAFT RETURNED TO SERVICE (TC NR 20061004005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H72 3O4  TRTA59EU   E26NE   5  CPZONE    
20061208000822006120800082EA  2006       12         8          CA061004006      220061001G8520                BEARING                                 PIPER PA31  PA31350     7103110SO  LYC   O540  LTIO540J2BD 41533EA                              CRANKSHAFT      BROKEN          W      A   UNSCHED LANDING                                                                                 Y  ENGINE STOPPAGE                                                               CRCRUISE         1                      CA       8542 1341                          L251768A                    (CAN) THE AIRCRAFT DEPARTED THE RUNWAY FOR A 1 HOUR TRIP. APPROXIMATELY 17 MINUTES INTO THE CRUISE PORTION OF FLIGHT THE PILOT NOTICED A LOSS IN OIL PRESSURE FOLLOWED BY NOISE FROM THE RT ENGINE. THE PILOT IMMEDIATELY FEATHERED THE PROP AND SHUTDOWN THE ENGINE. THE WEATHER WAS OK AND ELECTED TO RETURN TO THE DEPARTURE RUN-WAY AND LANDED WITHOUT INCIDENT. AN INVESTIGATION REVEALED THAT THE CRANKSHAFT BROKE AT THE NR 2 BEARING JOURNAL. (TC NR 20061004006)                                                                                                                                                                                                                                                                       1L72 3O3  O  A20SO   E14EA                
20061208000832006120800083SW  2006       12         8          CA061004007      120061002G5302206020113       INSERT                                  BELL  206   206B        1181511SW  ALLSN 250C  250C20B     03013GL                              VERTICAL STAB   CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       13000                                                          (CAN) IN COMPLIANCE WITH CF-2006-12 THE VERTICAL FIN WAS INSPECTED WITH 10X MAGNAFLYING GLASS AND THEN WAS LPI INSPECTED AND A CRACK WAS FOUND ON ONE OF THE INSERTS. THE FIN WAS SENT OUT FOR REPAIR. (TC NR 20061004007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3U3  U  H2SW    E4CE                 
20061208000842006120800084EA  2006       12         8          CA061004008      220060930G7240310926302       DUCT                                    DHAV  DHC3  DHC3        2800202EA  PWA   PT6   PT6A34      52043EA                              ENGINE          DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            1677                                                      (CAN) DURING A REGULARLY SCHEDULED HOT SECTION INSPECTION A CRACK WAS NOTICED IN THE LARGE EXIT DUCT (LED) BEING REMOVED FROM THE ENGINE.  THE CRACK WAS LOCATED ON THE DOME AT THE DOUBLE WALL SEAM.  THE LED HAD BEEN RECENTLY OVERHAULED AND HAD A TSO OF 1676.9.  THIS WAS THE 4TH LED DUCT THAT THIS OPERATOR HAS HAD A PROBLEMS WITH. (TC NR 20061004008)                                                                                                                                                                                                                                                                                                                                                                                 1H71 3R4  T  A815    E4EA                 
20061208000862006120800086EA  2006       12         8          CA061004009      120061004G3200                WASHER                                  DHAV  DHC6  DHC6        2802606EA                                                               MLG             MISMANUFACTURED W      O   OTHER                                                                                           W  INADEQUATE Q C                                                                NRNOT REPORTED   1                      CA                                                                      (CAN) WE HAVE FOUND 2 BATCHES OF C6U1156-27 MAIN LANDING GEAR WASHERS MADE FROM ALUMINUM LAMINATED SHIM MATERIAL, BUT SHOULD HAVE BEEN MADE FROM STAINLESS STEEL SHIM MATERIAL.  DUE TO THE APPLICATION OF THE WASHER, THERE IS NO STRENGTH REQUIREMENT, HOWEVER, THERE IS A POTENTIAL FOR GALVANIC CORROSION. THE AFFECTED BATCHES OF WASHERS ARE WO-25363/1 AND PO43141/69.  (TC NR 20061004009)                                                                                                                                                                                                                                                                                                                                              1H72 3T    RTA9EA                         
20061208000882006120800088    2006       12         8          CA061005001      120061005G3000                LINE                                                                       PWA   JT15  JT15D4      52112NE                              ANTI ICE SYS    DAMAGED         W      O   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      CA       7161 858                                                       (CAN) SEE REPORT ATTACHED  GAS GENERATOR DISPLAYED VISIBLE SIGNS OF COKED OIL ON THE EXTERNAL CASING. ENGINE OIL LEAK WAS CAUSED BY ANTI-ICING STEEL TUBE DEBONDING FROM THE INTERMEDIATE CASE CASTING AT THE STEEL TAB USED TO LOCATE THE TUBE DURING THE CASTING PROCESS. THE TAB PROTRUDES INTO THE OIL TANK AND IF DEBONDED CAN CAUSE OIL LEAKAGE.  ENGINEERING REPORT ATTACHED TO THIS SDR. (TC NR 20061005001)                                                                                                                                                                                                                                                                                                                                   4  F          E1NE                 
20061208000912006120800091CE  2006       12         8          CA061005002      120061005G57400513006142      RIVET                                   CESSNA185   A185E       2072818CE  CONT  O520  IO520D      17032SO  MCAULY2A34C D2A34C58    GL  FITTING         LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       7171                                                           (CAN) THE AIRCRAFT WAS DISASSEMBLED. IT WAS NOTED THAT THERE WERE SEVERAL LOOSE AND SMOKING FASTENERS THROUGH RT AFT WING FITTING BRACKET IN FUSELAGE. REFERENCED MFG PART MANUAL P527-12 FIGURE 30 INDEX NR 99.  (TC NR 20061005002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1H71 3O3  O  3A24    E5CE    5  CP3EA     
20061208000932006120800093NE  2006       12         8          CA061005003      220061005G8530                INTAKE DUCT                             DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE  HAMSTD2D    2D30        NE  ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) 5 OF THE 9 INTAKE TUBES WERE FOUND CRACKED AT THE CYLINDER FLANGE. (TC NR 20061005003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H71 3R3  RRCA806    5E1     5  CP206     
20061208000952006120800095NE  2006       12         8          CA061005005      220060925G73001851M43P08      ECU                                     AIRBUSA340  A340313            EU  CFMINTCFM56 CFM565C4    13802NE                              NR 2 ENGINE     FAILED          W      EF  ENGINE SHUTDOWN         ACTIVATE FIRE EXT.                                                      J  WARNING INDICATION                                                            CRCRUISE         1                      CA       33115                              741568                      (CAN) DEPARTURE AND ENROUTE TO DESTINATION, NR 2 ENGINE PARAMETERS ERRATIC, THEN INDICATE THAT NR 2 EGT OVER LIMITS, THEN VIBRATION.  ENGINE SHUTDOWN AND BOTTLE DISCHARGED. REPLACED ECU IAW MM, RT VSV ACTUATOR REPLACED.  FADEC MOTORING CHK ACCOMPLISHED IAW MM, MIN IDLE LEAK CHK ACCOMPLISHED IAW MM, PWR ASSURANCE CHK ACCOMPLISHED IAW MM, VIBE SURVEY CHK ACCOMPLISHED IAW MM,  CHK ACCOMPLISHED IAW MM.  ALL CHECKS OK, ENGINE OPS WITHIN NORMAL PARAMETERS. (TC NR 20061005005)                                                                                                                                                                                                                                                      2L74 4F4  FRTA197    E37NE                
20061208000972006120800097NM  2006       12         8          CA061005006      120061004G243523088002A       STARTER GEN                             DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  NR 2            FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            413                                                       (CAN) THE FLIGHT CREW SNAGGED THAT THE NR 2 GENERATOR FAILED. UPON FURTHER INVESTIGATION MAINTENANCE DISCOVERED THAT STARTER-GENERATOR HAD FAILED INTERNALLY. WHEN THE STARTER-GENERATOR IS COOLING DUCT AND WINDOW STRAP WERE REMOVED LOSE PIECES OF BRUSH MATERIAL FELL OUT OF THE STARTER-GENERATOR. ONE OF THE COMMUTATOR SEGMENTS WAS ALSO PARTIALLY MISSING AND MANY BRUSHES WERE CRACKED OR BROKEN. ONE OF THE DC CURRENT LIMITERS IN THE DC CONTACTOR BOX WAS ALSO FOUND TO BE OPEN. THE STARTER-GENERATOR, GENERATOR CONTROL UNIT, AND THE ASSOCIATED CURRENT LIMITER WERE REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20061005006)                                                                                      2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20061208001012006120800101EA  2006       12         8          CA061005007      120061004G3244900012001       TIRE                                    CNDAIRCL600 CL600*             EA  GE    CF34  CF348C1          NE                              MLG             FAILED          W      C   ABORTED TAKEOFF                                                                                 E  VIBRATION/BUFFET                                                              TOTAKEOFF        1                      CA       455                                                            (CAN) THE CREW REPORTED THAT DURING THE TAKEOFF ROLL THE FLIGHT ATTENDANT REPORT A LOUD BANG. AFTER CONFERENCING WITH MAINTENANCE CONTROL, THE AIRCRAFT WAS ASKED TO CONTINUE TO DESTINATION. UPON ARRIVAL, IT WAS DETERMINED THAT THE NR 4 MAIN WHEEL WAS RAGGED AND APPEARED DEFLATED. THIS IS THE SECOND (WILKERSON RETREAD) FOR THE CRJ 700/900 AS DOCUMENTED IN SDR 20060110004. (TC NR 20061005007)                                                                                                                                                                                                                                                                                                                                       2L72 4F4  FRTA21EA   EOOO63EN             
20061208001072006120800107EU  2006       12         8          CA061005009      120061004G5280                BOLT                                    EMB   ERJ190ERJ190100IGW3260408EU                                                               LT MLG DOOR     SHEARED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) LT MLG STAY AND DOOR BRACKET BOLTS SHEARED.  OLD BOLTS HAVE P/N 2821-8041, AND THE NEW BOLTS HAVE P/N NAS6605D28 (BETTER QUALITY).  THEY ARE BEING INSTALLED THROUGH SB 190-32-0010. (TC NR 20061005009)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F    RTA57NM                        
20061208001102006120800110EA  2006       12         8          CA061005010      220060909G7321                SHAFT                                   BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  NR 2 FMU        SHEARED         W      BA  EMER. DESCENT           UNSCHED LANDING                                                         XJ ENGINE FLAMEOUT           WARNING INDICATION                                  DEDESCENT        1                      CA       5602       F48358                                              (CAN) DURING DESCENT INTO BASE, NR 2 ENGINE SUDDENLY SHUTDOWN. CREW GOT THE INDICATION BY A YAW AND DISCOVERED AFTERWARDS THE PROP TQ WAS ZERO.  EMERGENCY DECLARED. POWERPLANT MESSAGE ON ED QRH ACTIONS WERE CARRIED OUT.  PAX BRIEFED ON DESCENT AND IN TERMINAL AFTERWARDS. UNEVENTFUL APPROACH/LANDING AND TAXI. MAINT REPORT: FAULT CODES: 360/907/935/970. FMU REMOVED AND FOUND SHAFT SHEARED. FMU REPLACED EGR CARRIED OUT NORMAL. (TC NR 20061005010)                                                                                                                                                                                                                                                                                 2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
20061208001112006120800111    2006       12         8          CA061005011      420060914G6122                GOVERNOR                                CESSNA206   U206G       2073356CE  CONT  O520  IO520F      17032SO  HARTZLHCJ3Y PHCJ3YF1    GL  PROPELLER       SEIZED          W      A   UNSCHED LANDING                                                                                 YJ ENGINE STOPPAGE           WARNING INDICATION                                  CRCRUISE         1                      CA                                                      051411          (CAN) THE A/C WAS IN NORMAL FLIGHT AND NOTED AN OVERSPEED CONDITION FROM CRUISE RPM TO FULL POWER.  CYCLING THE PROP PITCH CONTROL DID NOTHING; THE PILOT EXECUTED A FORCED LANDING.  AME REMOVED THE PROP GOVERNOR AND NOTICED IT WAS SEIZED AND CONTAMINATED. REMOVED THE OIL FILTER AND NOTICED IT WAS CONTAMINATED WITH METAL PARTICLES. DRAINED THE OIL PAN WITH FRESH VARSOL AND FLUSHED THE PAN TO CLEAN ANY CONTAMINATES.  INSTALLED FRESH NEW OIL AND INSTALLED NEW GOVERNOR.  GROUND RUN UP WAS SATISFACTORY FOR FERRY FLIGHT TO REQUIRED BASE. PROP AND ENGINE REMOVED DUE TO OVERSPEED AND SENT TO REPAIR STATION FOR INSPECTION. (TC NR 20061005011)                                                                               1H71 3O3  O  A4CE    E5CE    5  CP36EA    
20080220000032008022000003EU  2008       2          20         CA061005012      120061005G6200355A27008200    LEVER                                   SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1   60053NE                              LOAD COMPENSATORDAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2315                                                           (CAN) LOAD COMPENSATOR ARM WAS FOUND TO HAVE ELONGATED ATTACHMENT HOLES. NEW LEVER INSTALLED. THE OLD LEVER HAS BEEN SENT TO MFG FOR EVALUATION AS TO WHAT MAY BE THE CAUSE OF THIS. SUSPECT EXCESSIVE FORCE APPLIED BY THE ACCUMULATOR. (TC NR 20061005012)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1G71 3U3  U  H9EU    E19EU                
20061211001562006121100156SW  2006       12         11         CA061006002      120061001G32502719087007      ACTUATOR                                SWRNGNSA226 SA226AT     8780405SW  GARRTTTPE331TPE33110UA  01514WP  HARTZLHCB3T HCB3TN5     GL  NOSE STEERING   MALFUNCTIONED   W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      CA                                                                      (CAN) MAINTENANCE WAS COMPLETING AN ENGINE CHANGE.  AN AME TAXI`D THE AIRCRAFT FROM THE HANGER TO THE DESIGNATED RUNUP AREA.  ON THE TAXI WAY, THE AIRCRAFT ABRUPTLY VEERED TO THE RT, AND THE RT PROPELLER STRUCK A TAXIWAY MARKER.  THE ENGINE WAS SHUTDOWN AND DAMAGE WAS EVIDENT TO THE PROPELLER.  THE ENGINE AND PROPELLER WERE REPLACED.  THE NWS SYSTEM WAS TROUBLESHOT, NO ELECTRICAL CONTROL FAULTS WERE EVIDENT.  THE NWS DID FAIL ON A SUBSEQUENT GROUND RUN WITH ANOTHER AME.  ALL NWS COMPONENTS AT THE NOSE GEAR WERE REPLACED WITH SERVICEABLE PARTS - ACTUATOR, MANIFOLD, PRESSURE SWITCH, SERVO VALVE.  NO FAULTS WERE NOTED ON TAXI TESTS OR TEST FLIGHTS. (TC NR 20061006002)                                               2L72 4T4  TRTA5SW    E4WE    6  CP15EA    
20061211001582006121100158EA  2006       12         11         CA061006003      220060901G7321                DRIVE SHAFT     HAMSTD                  BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                              FMU             FRACTURED       W      O   OTHER                                                                                           XJ ENGINE FLAMEOUT           WARNING INDICATION                                  DEDESCENT        1                      CA                  F48358                                              (CAN) ON DESCENT, THE ENGINE FLAMED OUT.  GROUND INSPECTION REVEALED A FRACTURED FUEL METERING UNIT DRIVE SHAFT. (TC NR 20061006003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2H72 4T4  TRTA13NM   E00062EN             
20061211001592006121100159NE  2006       12         11         CA061006004      220060904G7230                ENGINE                                  BELL  212   212         1181420SW  PWA   PT6T  PT6T3B      52045NE                                              FIRE            W      F   ACTIVATE FIRE EXT.                                                                              AJ FLAME/FIRE                WARNING INDICATION                                  NRNOT REPORTED   1                      CA                                          61956                       (CAN) DURING FLIGHT THE FIRE WARNING ACTIVATED. THE FIRE BOTTLES WERE DISCHARGED AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED A PUNCTURED GAS GENERATOR CASE AND FIRE DAMAGE TO THE ENGINE.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 4U4  U  H4SW    E22EA                
20061211001612006121100161EA  2006       12         11         CA061006005      220060831G7314                COUPLING                                PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A6       52043EA                              PUMP            FRACTURED       W      O   OTHER                                                                                           J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      CA       2254                                                           (CAN) THE ENGINE EXPERIENCED AN UNCOMMANDED ACCELERATION IN FLIGHT.  THE ENGINE WAS SHUTDOWN AND SUCCESSFULLY RE-LIT AND THE UNCOMMANDED ACCELERATION REPEATED.  THE ENGINE WAS AGAIN SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED A FRACTURED FUEL CONTROL / FUEL PUMP COUPLING. (TC NR 20061006005)                                                                                                                                                                                                                                                                                                                                                                                                                                    1L71 3T3  TRTA78EU   E4EA                 
20061211001632006121100163EA  2006       12         11         CA061006006      220060719G7321                DRIVE SHAFT                             BEECH 90    C90         1152913CE  PWA   PT6   PT6A21      52043EA                              FUEL CONTROL    FRACTURED       W      O   OTHER                                                                                           XJ ENGINE FLAMEOUT           WARNING INDICATION                                  NRNOT REPORTED   1                      CA       2254       A75829                                              (CAN) THE FUEL CONTROL DRIVE SHAFT WAS FOUND FRACTURED.  THE FUEL CONTROL MID LIFE INSPECTION WAS DETERMINED NOT TO HAVE BEEN PERFORMED. (TC NR 20061006006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L72 3T4  T  3A20    E4EA                 
20061211001642006121100164NE  2006       12         11         CA061006007      220060824G7261                PRECOOLER                               AEROSPATR72 ATR72              EU  PWA   PW120 PW124B           NE                              ENGINE          UNKNOWN         W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      CA                                          124481                      (CAN) THE ENGINE LOW OIL PRESSURE WARNING ACTIVATED DURING A FLIGHT TEST.  THE ENGINE WAS SHUTDOWN IN FLIGHT.  THE FUEL-COOLED-OIL-COOLER AND FUEL HEATER WERE SUBSEQUENTLY REPLACED.  MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061006007)                                                                                                                                                                                                                                                                                                                                                                                                                                                         2H72 4T4  TRT        E2ONE                
20061211001652006121100165NE  2006       12         11         CA061006008      220060811G7200                ENGINE                                  BELL  212   212         1181420SW  PWA   PT6T  PT6T3B      52045NE                              NR 2            UNKNOWN         W      O   OTHER                                                                                           RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  HOHOVERING       1                      CA                                          62572                       (CAN) ON TRANSITION FROM HOVER, NR 2 POWER SECTION TORQUE DECREASED UNCOMMANDED.  AN EMERGENCY LANDING FOLLOWED RESULTING IN AIRFRAME DAMAGE.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061006008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1G71 4U4  U  H4SW    E22EA                
20061211001672006121100167NE  2006       12         11         CA061006009      220060908G7200                ENGINE                                  LEAR  60    60LEAR      5170707CE  PWA   305   PW305A      52128NE                                              FLAMED OUT      W      O   OTHER                                                                                           XJ ENGINE FLAMEOUT           WARNING INDICATION                                  DEDESCENT        1                      CA                                          CA0090                      (CAN) THE ENGINE FLAMED OUT ON DESCENT.  AN INFLIGHT RELIGHT WAS SUCCESSFULLY ACCOMPLISHED.  MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061006009)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA10CE   E35NE                
20061211001682006121100168NE  2006       12         11         CA061006010      220060913G7310                MANIFOLD                                CESSNA500   560CESSNA   2076750CE  PWA   530   PW535A           NE                              FUEL SYSTEM     LEAKING         W      FE  ACTIVATE FIRE EXT.      ENGINE SHUTDOWN                                                         KA FLUID LOSS                FLAME/FIRE                                          DEDESCENT        1                      CA                                                                      (CAN) A LOUD NOISE AND A FLASH FROM THE ENGINE WERE REPORTED ON DESCENT ACCOMPANIED BY A FIRE DETECTOR WARNING.  THE ENGINE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED SEPARATION OF THE NACELLE COWLS WITH RESULTANT AIRFRAME IMPACT DAMAGE.  THE ENGINE FUEL MANIFOLD AND EXTERNALS WERE FOUND TO BE FIRE DAMAGED.  MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061006010)                                                                                                                                                                                                                                                                                                           2L72 4F4  FRTA22CE   E00053EN             
20061211002052006121100205NE  2006       12         11         CA061006012      220060918G7261                ENGINE                                  BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE                                              LEAKING         W      E   ENGINE SHUTDOWN                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CLCLIMB          1                      CA                                          114348                      (CAN) DURING TAKE-OFF CLIMB, THE ENGINE LOW OIL PRESSURE WARNING ACTIVATED AND OIL PRESSURE DECREASED TO ZERO.  THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  INSPECTION REVEALED OIL IN THE ENGINE EXHAUST DUCT.  MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061006012)                                                                                                                                                                                                                                                                                                                                                                                       2L72 4T4  TRTA24CE   E26NE                
20061211002062006121100206NE  2006       12         11         CA061006013      220060815G7230                COMPRESSOR                              CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE                              ENGINE          SEIZED          W      O   OTHER                                                                                           XJ ENGINE FLAMEOUT           WARNING INDICATION                                  CRCRUISE         1                      CA                                          19374                       (CAN) THE ENGINE WAS REPORTED TO EMIT A LOUD NOISE AND SUBSEQUENTLY FLAMED OUT IN FLIGHT.  POST-FLIGHT INSPECTION REVEALED METAL DEBRIS IN THE OIL, RUBBING NOISES FROM THE POWER SECTION AND A SEIZED COMPRESSOR.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061006013)                                                                                                                                                                                                                                                                                                                                                                                                                               1H71 3T3  T  A37CE   E4EA                 
20070108001442007010800144NE  2007       1          8          CA061006014      220060919G7200                BLADE                                   AMTR  ALPHA ALPHA       05613GUGL  PWA   306   PW306B           NE                              ENGINE          DAMAGED         W      O   OTHER                                                                                           XJ ENGINE FLAMEOUT           WARNING INDICATION                                  CLCLIMB          1                      CA                                          CD0130                      (CAN) ON CLIMB, THE ENGINE EMITTED A LOUD NOISE AND FLAMED OUT.  SUBSEQUENT INSPECTION REVEALED HPT1 BLADE DAMAGE.  P&WC WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061006014)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1D71 3I4  FRTEXPA1D71E35NE                
20061211002072006121100207NE  2006       12         11         CA061006015      220060920G7261                ENGINE                                  CESSNA560   560XL       2076702CE  PWA   545   PW545A           NE                                              LEAKING         W      E   ENGINE SHUTDOWN                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA                                          DB0238                      (CAN) IN CRUISE, ENGINE OIL PRESSURE WAS SEEN TO DECREASE AND THE LOW OIL PRESSURE WARNING ACTIVATED.  THE ENGINE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED EXTERNAL OIL LEAKAGE.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061006015)                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F4  FRTA22CE   E00059EN             
20061211002082006121100208EA  2006       12         11         CA061006016      220060615G7210                PLANETARY GEAR                          BEECH 1900  1900C       1154161CE  PWA   PT6   PT6A65B     52043EA  HARTZLHCB4M HCB4MP3     GL  RGB             WORN            W      E   ENGINE SHUTDOWN                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB, ENGINE POWER FLUCTUATED ACCOMPANIED BY AN INCREASE IN ITT TEMPERATURE AND LOW OIL PRESSURE.  THE ENGINE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INVESTIGATION REVEALED FIRST STAGE PLANETARY GEAR DISTRESS. (TC NR 20061006016)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4T4  TRTA24CE   E4EA    6  CP56GL    
20061211002092006121100209NE  2006       12         11         CA061006017      220060909G7261                ENGINE                                  BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE  HARTZLHCE4A HCE4A3I     NE                  LEAKING         W      E   ENGINE SHUTDOWN                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA                                          PS0145                      (CAN) IN FLIGHT THE ENGINE LOST OIL PRESSURE.  THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT-OF-DEPARTURE.  POST-FLIGHT INSPECTION REVEALED A LOW ENGINE OIL LEVEL AND NOISES FROM THE ENGINE POWER SECTION ON ROTATION.  MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061006017)                                                                                                                                                                                                                                                                                                                                                                                             2L72 4T4  TRTA24CE   E26NE   5  CP10NE    
20061211002102006121100210NE  2006       12         11         CA061006018      220060927G7200                ENGINE                                  CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE                                              FIRE            W      D   RETURN TO BLOCK                                                                                 AJ FLAME/FIRE                WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA                                                                      (CAN) ON TAXI FOLLOWING LANDING, FLAMES WERE SEEN COMING FROM THE ENGINE EXHAUST.  MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061006018)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3T3  T  A37CE   E4EA                 
20061211002112006121100211NE  2006       12         11         CA061006019      220060927G7321                BEARING CAGE                            CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE                              FUEL CONTROL    FRACTURED       W      O   OTHER                                                                                           RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA                  C65140                                              (CAN) ENGINE TORQUE WAS SEEN TO FLUCTUATE IN CRUISE, REDUCING TO ZERO UNCOMMANDED DURING DESCENT. POWER WAS RECOVERED USING THE FUEL CONTROL MANUAL OVER-RIDE SYSTEM.  ON A SUBSEQUENT START THE ENGINE ACCELERATED UNCOMMANDED.  SUBSEQUENT INSPECTION REVEALED A PRE-SB1561 FCU BEARING CAGE FRACTURE. (TC NR 20061006019)                                                                                                                                                                                                                                                                                                                                                                                                                    1H71 3T3  T  A37CE   E4EA                 
20061211002122006121100212EA  2006       12         11         CA061006020      220060925G7200                ENGINE                                  SOCATATBM   TBM700      8682000EU  PWA   PT6   PT6A64           EA                                              SEIZED          W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                          111106                      (CAN) ENGINE OIL TEMPERATURE WAS SEEN TO INCREASE IN FLIGHT ACCOMPANIED BY A LOSS OF OIL PRESSURE.  THE ENGINE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED OIL IN THE ENGINE DRAINS AND SEIZURE OF THE POWER SECTION.  MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061006020)                                                                                                                                                                                                                                                                                                                                                                                                           1L71 3T4  TRTA60EU   E4EA                 
20061211002132006121100213SW  2006       12         11         CA061006021      120061004G6320                SHAFT           BELL        206040004101BELL  206   206L        1181522SW                                                               TRANSMISSION    FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       4049 4049  BMC00615                                            (CAN) EXCESSIVE CORROSION ON SHAFT. (TC NR 20061006021)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1G71 3U      H2SW                         
20061211002142006121100214CE  2006       12         11         CA061010001      120061003G57120513006142      BULKHEAD                                CESSNA185   A185F       2072821CE  CONT  O520  IO520D      17032SO  HARTZLHCC3Y HCC3YF1     GL                  DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3535                                                           (CAN) AT INSPECTION, SMOKING FASTENERS AT THE LT WING AFT FITTING WERE FOUND.  FASTENERS WERE REPLACED AS REQUIRED. (TC NR 20061010001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1H71 3O3  O  3A24    E5CE    5  CP25EA    
20061211002152006121100215EU  2006       12         11         CA061010002      120061010G32505325012044      BEARING                                 PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  MLG FORK        TWISTED         W      O   OTHER                                                                                           E  VIBRATION/BUFFET                                                              LDLANDING        1                      CA                                                                      (CAN) AFTER LANDING, CREW REPORTED TO MAINTENANCE THAT THEY HAD A HARD SHIMMY IN THE RUDDER PEDALS.  UPON INSPECTION WE FOUND THE NOSE STEERING BRACKETS BENT AND THE SPRING STRUT UNABLE TO MOVE.  THE STEERING STRUT CONNECTED TO THE STEERING HAD FAILED CAUSING THE FORK BEARING TO TWIST.  THE BENT BRACKET WAS REPLACED AND THE SPRING STRUT WAS SERVICED.  THE SYSTEM WAS FUNCTION CHECKED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20061010002)                                                                                                                                                                                                                                                                                 1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20061211002162006121100216CE  2006       12         11         CA061010003      120061010G304026106731        LINE                                    CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE  MCAULY3AF34C3GFR34C703  GL  DE ICE          CHAFED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) WIRE BUNDLE SECURED INCORRECTLY LEADING TO CHAFING ON/THRU PNEUMATIC DEICE AIR SUPPLY LINES. DURING THE INITIAL COMPLETION OF THE DEICE SYSTEM TEST AND SERVICE IT WAS FOUND THAT THE WIRING BUNDLE FOR THE DEICE SOLENOIDS AND PRESSURE SWITCHES HAD BEEN SECURED IN A POSITION WHICH ALLOWED THEM TO CONTACT SUPPLY LINE P/N 261067-31, WEARING A HOLE IN THE LINE AND DAMAGING SEVERAL WIRES. DEICE PIPES P/N 2601067-31 AND -32 WERE REPLACED.  WIRING WAS REPAIRED, REROUTED AND PROTECTED TO PREVENT FURTHER CONTACT WITH DEICE PIPES.  THE AIRCRAFT WAS RETURNED TO SERVICE. OTHER AIRCRAFT IN THE FLEET WERE INSPECTED WITH NO FAULTS FOUND.    (TC NR 20061010003)                                                               1H71 3T3  T  A37CE   E4EA    5  CP60GL    
20061211002172006121100217NM  2006       12         11         CA061010004      120060927G5512184T10071       SKIN            BOEING                  BOEING767   767233      1385113NM  PWA   JT9   JT9D7R4D    52054NE                              HORIZONTAL STAB DELAMINATED     W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       73006                                                          (CAN) LT HORIZONTAL STAB LEADING EDGE PANEL 332CL INNER SKIN COMPLETELY DELAMINATED. DELAMINATED SKIN WEARING INTO VERTICAL STIFFENERS LOCATED ALONG FRONT SPAR. (TC NR 20061010004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F4  FRTA1NM    E3NE                 
20061211002182006121100218EA  2006       12         11         CA061010005      120061009G2750                FLAP SYSTEM                             CNDAIRCL601 CL6012A12   1900303EA  GE    CF34  CF343A      30015NE                              TE FLAPS        MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 F  FLT CONT AFFECTED                                                             CLCLIMB          1                      CA                                                                      (CAN) FLAP FAIL BETWEEN 20 DEGREES TO 0 DEGREE DURING RETRACTION OF THE FLAPS AT TAKEOFF , FLAPS RESET ON GROUND IAW OPERATING MANUAL NR 1 ABNORMAL PROCEDURE SECTION 10 P3-4.  A/C RETURN TO SERVICE. NO SNAG.  FLAP FAIL BETWEEN 20 DEGREES TO 0 DEGREE DURING RETRACTION OF THE FLAPS AT TAKEOFF, FLAPS RESET ON GROUND IAW OPERATING MANUAL NR 1 ABNORMAL PROCEDURE SECTION 10 P3-4. A/C RETURN TO SERVICE. NO SNAG.  (TC NR 20061010005)                                                                                                                                                                                                                                                                                                   2L72 4F4  FRTA21AE   E15NE                
20061211002192006121100219NE  2006       12         11         CA061010006      220060913G7310305262701       MANIFOLD                                CESSNA500   560CESSNA   2076750CE  PWA   530   PW535A           NE                              FUEL SYSTEM     FAILED          W      E   ENGINE SHUTDOWN                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  DEDESCENT        1                      CA       2117                               DC0045                      (CAN) THE PILOTS HEARD A LOUD NOISE FOLLOWED BY A MOMENTARY FIRE WARNING LIGHT.  THE PILOTS SHUT THE ENGINE DOWN AND RETURNED TO BASE.  AFTER LANDING THE COWLING FOR THE RT ENGINE WAS FOUND TO BE MISSING THE ENGINE DAMAGED BY FIRE AND THE TAIL DAMAGED. (TC NR 20061010006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F4  FRTA22CE   E00053EN             
20061211002202006121100220GL  2006       12         11         CA061010007      120061010G5511C2TP1A          SPAR            DHAV                    DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE  HAMSTD2D    2D30        NE  HORIZONTAL STAB CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3180       SA387                                               (CAN) DURING THE CF-91-42 INSPECTION THE FORWARD SPAR WAS FOUND CRACKED AT THE TOP OF THE TOP ATTACH HOLE FOR THE FORWARD ATTACH BRACKETS PN C2TP159/160.  (TC NR 20061010007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H71 3R3  RRCA806    5E1     5  CP206     
20061211002212006121100221WP  2006       12         11         CA061011001      220060829G720031030351        BEARING                                 MTSBSIMU2   MU2B60      5780460CE  GARRTTTPE331TPE33110    01514WP  HARTZLHCB4T HCB4TN5     GL  ENGINE          FAILED          W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CRCRUISE         1                      CA       5858                               P38328C                     (CAN) AN IN-FLIGHT SHUTDOWN WAS CARRIED OUT WHEN THE ENGINE STARTED TO SURGE AND THE NEGATIVE TORQUE SYSTEM (NTS) PULSE. UPON DISASSEMBLY AT AN ENGINE REPAIR FACILITY, IT WAS NOTED THAT THE CAUSE WAS PREMATURE WEAR AND SUBSEQUENT FAILURE OF THE DUAL P/N: 3103035-1 BEARINGS. FAILURE OF THIS BEARING SET CAUSED LOSS OF ENGAGEMENT BETWEEN THE SPUR GEAR P/N: 896804-2 AND THE MATING GEAR IN THE TORQUE SENSOR. THE INTEGRITY OF THE FCU DRIVE TRAIN WAS LOST AND THE ENGINE FAILED WHEN THE FUEL CONTROL STOPPED BEING DRIVEN. THE ENGINE IS BEING OVERHAULED AT THIS TIME.  IT IS TO BE NOTED THAT AN OIL SAMPLE WAS TAKEN 9.7 HOURS PRIOR TO THE FAILURE. THE SAMPLE CAME BACK (INSPECT THIS ENGINE IMMEDIATELY) ONE WEEK AFTER THE EN1H72 3T4  TRTA10SW   E4WE    6  CP40EA    
20061211002222006121100222SO  2006       12         11         CA061011002      120060830G55436345703         CONNECTOR       PIPER                   PIPER PA28  PA28180     7102808SO  LYC   O360  O360A4A     41514EA  SNSNCH76E   76EM8S5     EA  RUDDER TRIM ARM BROKEN          W      D   RETURN TO BLOCK                                                                                 F  FLT CONT AFFECTED                                                             CLCLIMB          1                      CA       3675                                                           (CAN) WHEN MANUAL RUDDER TRIM WAS APPLIED IN CLIMB THERE WAS NO RESPONSE. SUBSEQUENT INSPECTION FOUND THAT THE ARM THAT CONNECTS THE TRIM ACTUATOR TO THE RUDDER CONTROL ASSEMBLY HAD BROKEN OFF THE ASSEMBLY AT THE EDGE OF THE WELD.  THE COMPLETE RUDDER TRIM ARM ASSEMBLY WAS REMOVED AND REPLACED WITH A NEW UNIT SUPPLIED FROM MFG.  METAL FATIGUE IS SUSPECTED.  (TC NR 20061011002)                                                                                                                                                                                                                                                                                                                                                     1L71 3O3  O  2A13    E286    5  NP4EA     
20061211002232006121100223EA  2006       12         11         CA061011003      220060927G72004708849004      CONTROLLER                              PIPER PA31  PA31        7103102SO  LYC   O540  TIO540A2C   41532EA  HARTZLHCE3Y HCE3YR2A    GL  LT ENGINE       DEFECTIVE       W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA            686                                                       (CAN) DURING A FLIGHT, THERE WAS A LOSS OF LT ENGINE OIL PRESSURE. THE AFFECTED ENGINE WAS SHUTDOWN AND AN UNSCHEDULED LANDING ACCOMPLISHED. AFTER INVESTIGATION, THE DENSITY CONTROLLER WAS FOUND DEFECTIVE. THE SEAL WAS RUPTURED ON THE (INTAKE) SIDE AND OIL WAS LEAKING INTO THE ENGINE AIR INTAKE. (TC NR 20061011003)                                                                                                                                                                                                                                                                                                                                                                                                                    1L72 3O3  O  A20SO   E14EA   5  CP33EA    
20061211002242006121100224EU  2006       12         11         CA061011004      120061001G253072067002M       OVEN                                    AIRBUS330   A330243     3930330EU  RROYCERB211 RB211*      54555NE                              GALLEY          SMOKE           W      H   DEACTIVATE SYST/CIRCUITS                                                                        B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA                                                                      (CAN) BURNING SMELL WAS NOTICED IN THE FWD GALLEY BY THE FLIGHT ATTENDANT WITH AN ASSOCIATE ECAM SMOKE WARNING OF THE FWD LAVATORY. F/A NOTICED SMELL COMING FROM NR 3 OVEN TIMER. OVEN WAS SWITCHED OFF FOR THE REMAINING OF THE FLIGHT WITH NO FURTHER PROBLEM. AIRCRAFT WAS INSPECTED AT THE ARRIVAL STATION AND THE OVEN WAS DEACTIVATED.  OVEN WAS REPLACED ON ARRIVAL AT MAIN BASE. DURING SHOP INSPECTION THE OVEN OPERATION WAS NORMAL BUT A SMALL PIECE OF MELTED PLASTIC WAS FOUND AT THE FWD BOTTOM CORNER OF THE OVEN. OVEN WAS TESTED AND RETURNED TO SERVICE.  (TC NR 20061011004)                                                                                                                                                2L72 4F4  FRTA46NM   A12EU                
20061211002252006121100225EU  2006       12         11         CA061011005      120060929G5300A5247017100200  ACCESS PANEL                            AIRBUS310   A310300     3930305EU  GE    CF6   CF680C2*         GL                              FUSELAGE        MISSING         W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA                                                                      (CAN) UPON AIRCRAFT ARRIVAL, DURING WALK AROUND INSPECTION, FOUND THE FWD CARGO DOOR LOWER FWD ACCESS PANEL, FIN811AR, MISSING. MOUNTING HARDWARE, FASTENERS AND LANYARDS WERE STILL ATTACHED TO THE CARGO DOOR. DOOR WAS INSPECTED AND NO FURTHER DAMAGE WAS NOTICED. AIRCRAFT WAS DISPATCH UNDER CDL. NEW PANEL INSTALLED OCT5/06. (TC NR 20061011005)                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F4  FRTA35EU   E23EA                
20061211002512006121100251NM  2006       12         11         CA061011007      120060721G29136617303         PUMP                                    BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  NR 2 HYD SYSTEM CRACKED         W      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA       1576       K0294                                               (CAN) DURING CRUISE AT 18000 FT, (NR 2 HYD ISO VLV, NR2 ENG HYD PUMP) AND (ROLL SPLR OB HYD) CAUTION LIGHT WERE ILLUMINATED, AND THEN, NR 2 HYD PRESS DROPPED TO 0 PSI AND QUANTITY ALSO DROPPED TO 0. EMERGENCY LANDING CONDUCTED WITH ALTERNATE LDG EXTENSION. THE AIRCRAFT WAS TOWED TO PARKING SPOT. THE GROUND INSPECTION REVEALED THAT NR 2 EDP WAS CRACKED AND HAD A (1.5 X 1.0 CM) HOLE. METAL DEBRIS WAS FOUND IN ALL FILTERS (PRESS, RETURN AND CASE DRAIN), AND DPI FOR NR 2 CASE DRAIN FILTER WAS POPPED OUT. EDP REPLACED, HYDRAULIC SYSTEM FLUSHED. (TC NR 20061011007)                                                                                                                                                           2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
20061211002542006121100254NM  2006       12         11         CA061011008      120061004G2611473925          CONTROL UNIT                            BOEING737   7372L9      1384497NM  PWA   JT8   JT8D17      52049NE                              SMOKE DETECTION MALFUNCTIONED   W      D   RETURN TO BLOCK                                                                                 N  FALSE WARNING                                                                 TXTAXI/GRND HDL  1                      CA                                                                      (CAN) ON TAXI FOR DEPARTURE THE CREW OBSERVED A NR 2 CARGO PIT CAUTION INDICATION. THE AIRCRAFT RETURNED TO COMPANY RAMP WHERE MAINTENANACE DETERMINED THE SMOKE DETECTOR SYSTEM CONTROL ELECTRONICS UNIT IN THE NR 2 PIT WAS AT FAULT. THE UNIT WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20061011008)                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA16WE   E2EA                 
20061211002562006121100256NM  2006       12         11         CA061011009      120061004G324665446604        ACTUATOR                                BOEING737   737242C     1384478NM  PWA   JT8   JT8D9A      52048NE                              MLG             BYPASSING       W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) DURING DEPARTURE THE NOSE LANDING GEAR FAILED TO RETRACT. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WITHOUT FURTHER INCIDENT. MAINTENANCE FOUND THE NOSE LANDING GEAR GRAVEL DEFLECTOR ACTUATOR WAS BYPASSING. THE UNIT WAS REPLACED AND THE AIRCRAFT REURNED TO SERVICE. THE ACTUATOR REMOVED HAD BEEN REPLACED THE PREVIOUS DAY AND THE VENDOR HAS BEEN CONTACTED TO PROVIDE AN IMMEDIATE TEARDOWN REPORT. (TC NR 20061011009)                                                                                                                                                                                                                                                                                                        2L72 4F4  F  A16WE   E2EA                 
20061211002582006121100258SW  2006       12         11         CA061011010      120061004G6310CL422501        CLUTCH                                  BELL  206   206B        1181511SW  ALLSN 250C  250C20B     03013GL                              FREEWHEEL UNIT  CRACKED         W      E   ENGINE SHUTDOWN                                                                                 O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA       1927                                                           (CAN) 2 SPRAG RETAINER WERE CRACKED, THEREFORE ALLOWING MISALIGNMENT AND CAUSING A NOISE. (TC NR 20061011010)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1G71 3U3  U  H2SW    E4CE                 
20061211002622006121100262GL  2006       12         11         CA061011011      320061004G6110M5150021        FITTING         HARTZL                  CESSNA206   U206G       2073356CE  CONT  O520  IO520F      17032SO  HARTZLHCJ3Y PHCJ3YF1    GL  PROPELLER       OPEN            W      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CLCLIMB          1                      CA       1483       FP1078A                             FP1078A         (CAN) PILOT EXPERIENCED EXCESSIVE GREASE LEAKAGE ON WINDSCREEN DURING TAKEOFF AND CLIMB, RETURNED TO MAINTENANCE BASE IMMEDIATELY. ON INSPECTION ONE GREASE FITTING WAS FOUND DEFECTIVE. GREASE FITTING WAS REPLACED. PROP RE-GREASED IAW PROP OWNERS MANUAL, PN115N, CHAP6-6. A/C GROUND RUN + PROP LEAK CHECKED. NO FAULTS FOUND. A/C TEST FLOWN TO ENSURE NO LEAKAGE AT HIGH POWER SETTINGS AND FOR PROPER PROPELLER FUNCTION. CHECKED SERVICEABLE - 100HR PROPELLER INSPECTION AND LUBRICATION WAS C/O PRIOR TO FLIGHT ON OCT.3/06 (TC NR 20061011011)                                                                                                                                                                                      1H71 3O3  O  A4CE    E5CE    5  CP36EA    
20061211002642006121100264SW  2006       12         11         CA061011012      120061010G6730C4264278        GLAND NUT       TACTAIR                 BELL  206   206L4       1182110SW  ALLSN 250C  250C30P     03013GL                              SERVO ACTUATOR  CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3581       RH4576A                                             (CAN) DURING THE FIRST OVERHAUL OF THREE SERVO ACTUATORS 2 WERE FOUND TO HAVE CRACKS ON THE GLAND THAT RETAINS THE PISTON SEAL. BOTH SERVO ACTUATOR GLAND ASSEMBLIES WERE CRACKED IN THE SAME AREA.  (TC NR 20061011012)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1G71 3U3  UNCH2SW    E1GL                 
20061211002662006121100266NE  2006       12         11         CA061011013      220061007G7250597602A         TURBINE BLADES                          SKRSKYS64   S64E        8142604NE  PWA   JFTD12JFTD12A4A   52047NE                              ENGINE          BROKEN          W      A   UNSCHED LANDING                                                                                 EJ VIBRATION/BUFFET          WARNING INDICATION                                  DEDESCENT        1                      CA       2947                               672488                      (CAN) THE AIRCRAFT WAS INVOLVED IN AERIAL LOGGING OPERATIONS, ON A SHORT FINAL APPROACH TO THE LOG LANDING THE AIRCRAFT DEVELOPED A VERY NOTICEABLE HIGH FREQUENCY VIBRATION THAT WAS FELT BY THE FLIGHT CREW THROUGHOUT THE AIRCRAFT INCLUDING THE FLIGHT CONTROLS. THE VIBRATION WAS ALSO ACCOMPANIED BY A VERY LOUD GROWLING NOISE. A SCAN OF THE AIRCRAFT INSTRUMENTS REVEALED NOTHING ABNORMAL. THE PILOT ELECTED TO CONTINUE THE APPROACH TO DROP OFF THE LOAD AT THE LOG LANDING AND THEN MADE A PRECAUTIONARY LANDING AT A NEAR BY LOCATION ON THE BEACH OF THE LAKE. AFTER SHUTDOWN, AN EXTENSIVE INSPECTION OF THE ENTIRE AIRCRAFT CARRIED OUT BY MAINTENANCE PERSONNEL REVEALED A LARGE AMOUNT OF METAL PARTICLES FUSED TO THE INSIDE2G72 4U4  U  H4EA    E15EA                
20061211002682006121100268NE  2006       12         11         CA061011014      220061005G73221D1             FUEL CONTROL                            SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1        NE                                              LEAKING         W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA                                                                      (CAN) FUEL SMELL WAS REPORTED IN THE CABIN WHEN THE HEATER WAS TURNED ON.  FCU WAS REMOVED AND FUEL WAS FOUND IN THE P2 AIR CHAMBER WHEN THE FCU WAS INVERTED. FCU WAS REMOVED AND RETURNED TO MFG FOR REPAIRS.  FCU RAN 712.6 HRS SINCE LAST REPAIR. FCU P/N 2915145338508 S/N A969B (TC NR 20061011014)                                                                                                                                                                                                                                                                                                                                                                                                                                       1G71 3U3  U  H9EU    E19EU                
20061211002692006121100269EU  2006       12         11         CA061012001      120061012G2740200031800       CLUTCH                                  PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  PITCH SERVO     CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A ROUTINE PHASE INSPECTION, THE AREA AROUND THE PITCH SERVO IS INSPECTED.  DURING THIS, THE FRICTION PLATE WAS DISCOVERED TO BE CRACKED IN HALF.  THE PITCH SERVO CLUTCH WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20061012001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20061211002702006121100270    2006       12         11         CA061012002      420060526G3160C19190AB04      DISPLAY                                 BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  COCKPIT         SHORTED         W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA       1670                                                           (CAN) DURING FLIGHT, THE FLIGHT CREW REPORTED THAT THE COPILOT`S PFD WENT BLANK, THEN CAME BACK ON IN POST MODE (GREEN T) THEN WENT BLANK AGAIN PERMANENTLY, FOLLOWED BY A BURNING ODOR (NO VISIBLE SMOKE OR FLAMES). THE ODOR WAS CARRIED BY THE RECIRC FAN THROUGHOUT THE CABIN AND DETECTED BY THE FLIGHT ATTENDANTS. MECHANICS FOUND EVIDENCE OF SOOT AROUND THE COOLING HOLES OF THE REMOVED PFD. (TC NR 20061012002)                                                                                                                                                                                                                                                                                                                      2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
20061211002712006121100271EA  2006       12         11         CA061012003      120061011G27306229815704      CIRCUIT CARD                            CNDAIRCL600 CL6002B19   1900309EA                                                               ELEVATOR CONTROLFAILED          W      O   OTHER                                                                                           O  OTHER                                                                         CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB OUT, ENROUTE, CREW EXPERIENCED PITCH TRIM, MACH TRIM AND STAB TRIM CAUTION INDICATIONS. CREW THOUGHT THEY EXPERIENCED FLIGHT CONTROL ISSUES. AFTER SOURCING THE QUICK REFERENCE HANDBOOK, CREW ELECTED TO DIVERT, BEING THE CLOSEST SUITABLE AIRPORT. CREW DID CONTACT MAINTENANCE TO RESET SOME CIRCUIT BREAKERS AND ALSO DID HOLD WEST OF YFC FOR FUEL BURN OFF. CREW DID DECLARE AN EMERGENCY AND DID HAVE EMERGENCY VEHICLES STANDING BY. PASSENGER ANNOUNCEMENT WAS MADE TO THE EFFECT THAT AIRCRAFT WAS HAVING  A FLIGHT CONTROL PROBLEM HOWEVER EVERYTHING WAS UNDER CONTROL. PASSENGERS WERE ADVISED TO BRACE FOR LANDING. PASSENGER REACTION WAS NIL. FLIGHT LANDED SAFELY AND PASSENGERS DEPLANED. (TC NR 2006101202L72 4F    RTA21EA                        
20061211002722006121100272NE  2006       12         11         CA061012004      220061012G75103039936         GASKET          PWC                     BEECH 200   200BEECH    1152920CE  PWA   PT6   PT642A           NE  HARTZLHCE4N HCE4N3      NE  ENGINE          CRACKED         W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA                                                                      (CAN) GASKET PN 3007342 AND SUBSEQUENT SUPERCEDURE TO 3039936 ARE THE ONLY GASKETS SPECIFIED FOR USE ON THE CABIN BLEED AIR PORT. THE 3039936 GASKETS ARE MADE OF A FIBER OR OTHER MATERIAL NOT WELL SUITED TO THIS HOT AND HIGH PRESSURE AREA. OTHER ENGINES LIST A METAL GASKET OPTION PN 3029677 AS APPROVED FOR INSTALLATION AT THIS PORT. MFG HAS BEEN NOTIFIED OF THIS ISSUE IN THE -42 IPC. (TC NR 20061012004)                                                                                                                                                                                                                                                                                                                          1L72 4T4  T  A24CE   E4EA    5  CP10NE    
20061211002742006121100274NM  2006       12         11         CA061012005      120061008G3260858601          PSEU                                    DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF15      NE  PRXY SENSOR     WARNING LIGHT   W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      CA       301899400                                                      (CAN) AFTER TAKEOFF GEAR SELECTED UP , VISUALLY CONFIRMED GEAR WAS UP , INDICATION STILL SHOWED GEAR DOWN AND LOCKED (3 GREEN LIGHTS) , NORMAL GEAR EXTENSION AND AIRCRAFT RETURNED TO DEPARTURE AIRPORT FOR NORMAL LANDING. MAINTENANCE INSPECTION FOUND PSEU INTERNAL HISTORY SHOWING CARD FAULT . PSEU REPLACED. AIRCRAFT RETURNED TO SERVICE. (TC NR 20061012005)                                                                                                                                                                                                                                                                                                                                                                           2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20061211002752006121100275EU  2006       12         11         CA061013001      120061010G7500690200          DUCT SEAL                               AEROSPATR42 ATR42300    8680920EU  PWA   120   PW120            NE  HAMSTD14SF  14SF5       NE  BLEED AIR SYS   LEAKING         W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) ENROUTE THE CREW OBSERVED A BLEED AIR LEAK WARNING. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE AND LANDED WITH NO FURTHER PROBLEM. MAINTENANCE DETERMINED THAT A BLEED AIR SYSTEM DUCT SEAL HAD FAILED. THE AIRCRAFT IS AWAITING PARTS. (TC NR 20061013001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2H72 4T4  TRTA53EU   E20NE   6  CP7NE     
20061211002782006121100278EA  2006       12         11         CA061013003      120061011G5730                SKIN                                    DHAV  DHC6  DHC6        2802606EA  PWA   PT6   PT6A27      52043EA                              LT WING         DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN)  A MAINTENANCE FACILITY RECEIVED THESE RE-LIFED WINGS FROM RW MARTIN. INCOMING INSPECTION REVEALED A LT/RT BUCKLED TOP SKIN AND DAMAGED SHROUD SKINS. THE DAMAGE DOES NOT APPEAR TO BE SHIPPING RELATED. RW MARTIN WERE NOT ABLE TO SEND AN NDT REPORT FOR DELAMINATION OF BONDED UPPER SKINS THEREFORE THE MAINTENANCE FACILITY PROVIDED AN INDEPENDENT NDT SPECIALIST TO INSPECT THE WINGS. THE PICTURES REVEAL WHERE THE SKINS WERE FOUND DELAMINATED (COLORED SPOTS).  THE DELAMINATION IS MAINLY ON THE OB SKIN, WITH THE EXCEPTION OF 2 LOCATIONS: RT WING IB OF RIB WS 297.50 AND LT WING IB OF RIB WS 272.  (TC NR 20061013003)                                                                                                   1H72 3T4  TRTA9EA    E4EA                 
20061211002792006121100279EA  2006       12         11         CA061013004      120061011G5730                SKIN                                    DHAV  DHC6  DHC6        2802606EA  PWA   PT6   PT6A27      52043EA                              RT WING         DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) A MAINTENANCE FACILITY RECEIVED THESE RE-LIFED WINGS FROM RW MARTIN. INCOMING INSPECTION REVEALED A LT/RT BUCKLED TOP SKIN AND DAMAGED SHROUD SKINS. THE DAMAGE DOES NOT APPEAR TO BE SHIPPING RELATED. RW MARTIN WERE NOT ABLE TO SEND AN NDT REPORT FOR DELAMINATION OF BONDED UPPER SKINS THEREFORE THE MAINTENANCE FACILITY PROVIDED AN INDEPENDENT NDT SPECIALIST TO INSPECT THE WINGS. THE PICTURES REVEAL WHERE THE SKINS WERE FOUND DELAMINATED (COLORED SPOTS).  THE DELAMINATION IS MAINLY ON THE OB SKIN, WITH THE EXCEPTION OF 2 LOCATIONS: RT WING IB OF RIB WS 297.50 AND LT WING IB OF RIB WS 272.  (TC NR 20061013004)                                                                                                    1H72 3T4  TRTA9EA    E4EA                 
20061211002802006121100280NE  2006       12         11         CA061013005      220061008G7310J1175D0244AA    FUEL LINE                               CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              NR 1 ENGINE     LEAKING         W      D   RETURN TO BLOCK                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA       1043910439                                                     (CAN) RAMP CREW SERVICING AIRCRAFT REPORTED FUEL LEAKING FROM NR 1 ENGINE ON TAXI OUT. SHUTDOWN NR 1 ENGINE. FUEL DRIPPING FROM LOWER COWL. MAINTENANCE INSPECTION FOUND VARIABLE GUIDE VANE FUEL LINE LEAKING. LINE P/N J1175D0244AA REPLACED. LEAK CHECKED AND AIRCRAFT RETURNED TO SERVICE. NOTE: THIS PART IS NOT TRACKED AS A ROTABLE COMPONENT , TIMES PROVIDED ARE THE ENGINE INSTALLED TIMES . NR 1 ENGINE S/N 873093 , NR 1 ENGINE P/N 6089T11G01 (TC NR 20061013005)                                                                                                                                                                                                                                                                  2L72 4F4  FRTA21EA   E15NE                
20061211003042006121100304EA  2006       12         11         CA061013006      120061011G2750855D100         BPSU                                    CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              INTERNAL        MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA       4796 4796                                                      (CAN) ON SELECTING FLAPS FOR APPROACH (FLAP FAIL) MESSAGE DISPLAYED. DUE TO WEATHER CONDITION AIRCRAFT PROCEEDED WITH MISSED APPROACH. UNABLE TO RETRACT FLAPS.  AIRCRAFT DIVERTED TO NEAREST ALTERNATE AIRPORT WITH IMPROVED WEATHER , WITH FLAPS REMAINING EXTENDED AT 30 DEG.  IN-FLIGHT RESET PROCEDURE FOR FLAPS UNSUCCESSFUL. AFTER ARRIVAL AT ALTERNATE AIRPORT FLAP RESET PROCEDURE CARRIED OUT , FLAPS RETRACTED TO 8 DEG AND AIRCRAFT FERRIED TO MAINTENANCE BASE. MAINTENANCE REPLACED LT BRAKE AND POSITION SENSING UNIT. RIGGING AND FUNCTION CHECKS COMPLETED. AIRCRAFT RETURNED TO SERVICE. (TC NR 20061013006)                                                                                                                  2L72 4F4  FRTA21EA   E15NE                
20061211003072006121100307NM  2006       12         11         CA061014001      120061011G215039854021        VALVE                                   BOEING727   727243      138408DNM  PWA   JT8   JT8D9A      52048NE                              A/C PACK        FAILED          W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA                                                                      (CAN) AFTER DEPARTURE, CREW DISCOVERED THAT THE A/C WOULD NOT PRESSURIZE. A/C RETURNED TO BASE WHERE A PACK VALVE WAS FOUND FAILED IN THE CLOSED POSITION. VALVE WAS REPLACED AND A/C RETURNED TO SERVICE. (TC NR 20061014001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L73 4F4  FRTA3WE    E2EA                 
20061211003082006121100308NM  2006       12         11         CA061016001      120060821G2497                WIRE                                    DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF23      NE  AC POWER        BURNED          W      K   NONE                                                                                            B  SMOKE/FUMES/ODORS/SPARKS                                                      ININSP/MAINT     1                      CA       7115                                                           (CAN) AN OPERATOR EXPERIENCED AN EXTERNAL AC POWER PROBLEM THAT WAS TRACED TO SEVERAL BURNED WIRES AND A BLOWN (F4) FUSE.  IT IS DETERMINED THAT THE MOST PROBABLE CAUSE FOR THIS EVENT WAS THE (12 GAUGE) FEEDER CABLES CHAFING TOGETHER ON THE ADJACENT STRUCTURE. (TC NR 20061016001)                                                                                                                                                                                                                                                                                                                                                                                                                                                        2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20061205003052006120500305GL  2006       12         5          CA061016002      120061014G321358S9241         STRUT                                   DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE                              FLOATS          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING 100 HOUR INSPECTION, THE L/H MIDDLE FLOAT STRUT WAS FOUND TO HAVE A 4" STRESS CRACK EXTENDING DOWN THE LEADING EDGE FROM THE TOP OF THE STRUT.  THE AIRCRAFT IS OPERATED EXCLUSIVELY ON FLOATS IN A CORROSIVE ENVIRONMENT IN GENERALLY ADVERSE LANDING CONDITIONS.  TSN UNKNOWN. (TC# 20061016002)                                                                                                                                                                                                                                                                                                                                                                                                                                 1H71 3R3  RRCA806    5E1                  
20061211003102006121100310NE  2006       12         11         CA061016003      220061006G7200M8505237        CLAMP                                   SAAB  SF340 SF340A      7850100EU  GE    CT7TP CT75A2      30030NE  ROTOL R389  R3894123F25 NE  ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) ENGINE CONTROL CLAMP FOUND CRACKED ON ENGINE INSPECTION. REFERENCE AIRCRAFT IPC 71-00-02 FIG 15, ITEM NR 6 THE PART WAS NOT IDENTIFIED BY A SPECIFIC PN MARKED ON THE CLAMP.  SUSPECT POSSIBLE UNAPPROVED PART PREVIOUSLY INSTALLED. (TC NR 20061016003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4T4  TRTA52EU   E8NE6   6  CP30NE    
20061205003032006120500303GL  2006       12         5          CA061016004      120061014G321358S9242         STRUT                                   DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE                              FLOAT           CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING 100 HOUR INSPECTION THE RT REAR FLOAT STRUT WAS FOUND TO HAVE A 6` STRESS CRACK ORIGINATING AT THE TOP FORWARD SIDE OF THE STRUT. TIME IN SERVICE IS UNKNOWN.  TAT 22,057 HOURS.  THE AIRCRAFT IS OPERATED EXCLUSIVELY ON FLOATS IN A CORROSIVE ENVIRONMENT AND GENERALLY ADVERSE LANDING CONDITIONS. (TC# 20061016004)                                                                                                                                                                                                                                                                                                                                                                                                            1H71 3R3  RRCA806    5E1                  
20061211003122006121100312    2006       12         11         CA061016005      420061012G342179266941        GYRO                                    LKHEED382   382G        526414USO  ALLSN 501D  501D22A     03006GL  HAMSTD54H   54H60117    NE  COCKPIT         MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         DEDESCENT        1                      CA                                                                      (CAN) DURING DESCENT THE CREW OBSERVED A GYRO FLAG AND THE A/P DISENGAGED. THE COMPASS BEGAN TO OSCILLATE WITH A COMPARATOR FAIL LIGHT INDICATION.  THE AIRCRAFT RETURNED TO POINT OF DEPARTURE AND LANDED WITHOUT INCIDENT.  MAINTENANCE REPLACED THE NR 1 VG AND THE AIRCRAFT WAS RETURNED TO SERVICE AFTER SATISFACTORY GROUND TEST. (TC NR 20061016005)                                                                                                                                                                                                                                                                                                                                                                                     2H74 4T4  T  A1SO    E282    6  CP906     
20061211003132006121100313NE  2006       12         11         CA061016006      220061011G7230                CASE                                    DHAV  DHC8  DHC8103     1386005NM  PWA   PW121 PW121       52124NE  HAMSTD14SF  14SF7       NE  GAS GENERATOR   CRACKED         W      A   UNSCHED LANDING                                                                                 R  PARTIAL RPM/PWR LOSS                                                          CLCLIMB          1                      CA       2318714478                         120775                      (CAN) SHORTLY AFTER TAKE-OFF AT 500FT AGL THE CREW REDUCED POWER TO CLIMB POWER AND REALIZED THAT THE LT ENGINE ITT ROSE RAPIDLY TO APPROXIMATELY 850-900 DEGREES CELSIUS. THE OVER-TEMPERATURE LIGHT ILLUMINATED AND THE ENGINE OIL TEMPERATURE WAS ALSO RISING. THE ENGINE POWER WAS REDUCED TO STAY WITHIN LIMITS AND THE AIRCRAFT TURNED BACK TO LAND SAFELY WITHOUT INCIDENT. MAINTENANCE FOUND THAT THE ENGINE HAD DEVELOPED 2 SUBSTANTIAL CRACKS ON THE GAS-GENERATOR CASE.  THE CRACKS MEASURED APPROXIMATELY 3.5 INCHES IN LENGTH EACH AND WERE LOCATED AT APPROXIMATELY THE 11:30  AND 10 OCLOCK POSITIONS. IT SHOULD ALSO BE NOTED THAT THIS PORTION OF THE GAS GENERATOR CASE IS NORMALLY COVERED WITH AN INSULATION BLANKET. THE E2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20061205003042006120500304CE  2006       12         5          CA061016007      120061014G553404310093        ATTACH BRACKET                          CESSNA150   152         2071835CE  LYC   O235  O235L2C     41505EA                              VERTICAL STAB   CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       21277                                                          (CAN) ONE OF THE TWO VERTICAL TAIL ATTACH BRACKETS WAS DISCOVERED CRACKED APPROXIMATELY 90% OF ITS LENGTH DURING A SCHEDULED INSPECTION. THE CRACK LOCATION IS IN THE RADIUS WHERE THE VERTICAL LEG INTERSECTS THE HORIZONTAL LEG.   THERE IS A SERVICE LETTER WHICH DEALS WITH THIS, HOWEVER IT DOESNT APPLY TO THIS SERIAL NUMBER AIRCRAFT.  WE ARE REPLACING THE TWO ON THIS AIRCRAFT AS WELL AS ON THE OTHER C152 IN THE FLEET. (TC# 20061016007)                                                                                                                                                                                                                                                                                         1H71 3O3  ONT3A19    E223                 
20070129003252007012900325EU  2007       1          29         CA061017004      120061016G29109740926112      RELAY                                   PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  HYDRAULIC SYS   BURNED          W      K   NONE                                                                                            J  WARNING INDICATION                                                            LDLANDING        1                      CA       5042                                                           (CAN) FOLLOWING LANDING OF AIRCRAFT AMBER (HYD).  ANNUNCIATOR ILLUMINATED. INSPECTION OF HYDRAULIC MOTOR POWER RELAY MAIN CONTACTS INDICATED THE CONTACTS WERE SEVERLY BURNED. NEW RELAY INSTALLED ,FUNCTION TEST OF LANDING GEAR SYSTEM PERFORMED SATISFACTORY. (TC NR 20061017004)                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20061205002932006120500293SO  2006       12         5          CA061017005      120061016G3260                DOWNLOCK SWITCH                         LKHEED382   382G        526414USO  ALLSN 501D  501D22A     03006GL  HAMSTD54H   54H60117    NE  MLG             OUT OF ADJUST   W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      CA                                                                      (CAN) DURING DEPARTURE THE NOSE LANDING GEAR FAILED TO RETRACT ON TAKE-OFF. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WITHOUT FURTHER PROBLEM. MAINTENANCE ADJUSTED THE DOWNLOCK SWITCH AND CARRIED OUT A GEAR SWING BEFORE THE AIRCRAFT WAS RETURNED TO SERVICE.  (TC# 20061017005)                                                                                                                                                                                                                                                                                                                                                                                                                                                          2H74 4T4  T  A1SO    E282    6  CP906     
20061205003062006120500306    2006       12         5          CA061017006      420061013G83006014T81G26      GEARBOX                                 CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30015NE                              LT ENGINE       FAILED          W      A   UNSCHED LANDING                                                                                 Y  ENGINE STOPPAGE                                                               DEDESCENT        1                      CA                                                                      (CAN) LEFT ENGINE IN-FLIGHT SHUTDOWN DUE TO ACCESORIES GEARBOX (AGB)FAILURE. AGB BORESCOPE INSPECTION REVEALED A BROKEN GEAR. AIRFRAME HOURS=25499:54. CYCLES=21133. (TC# 20061017006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA21EA   E15NE                
20070129003262007012900326    2007       1          29         CA061017007      420061017G611304500391791     BULKHEAD                                CESSNA150   150H        2071818CE  CONT  O200  O200A       17020SO  MCAULY1A101 1A101DCM    GL  PROPELLER       CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3509                                                           (CAN) ON PILOT WALK AROUND THE SPINNER ASSY WAS NOTED TO BE LOOSE. UPON INSPECTION IT WAS OBSERVED THAT THE FWD SPINNER BULKHEAD WAS CRACKED. THIS WAS MOST LIKELY CAUSED BY PILOTS PUSHING ON THE SPINNER WHEN GROUND HANDLING THE AIRCRAFT. (TC NR 20061017007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1H71 3O3  O  3A19    E252    5  NP918     
20061205003072006120500307CE  2006       12         5          CA061018001      120061013G78001754001         EXHAUST RISER                           CESSNA172   172M        2072418CE  LYC   O320  O320E2D     41508EA  MCAULY1C160 1C160DTM    GL  NR 3            CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       150                                                            (CAN) THE (EXHAUST) FLANGE WAS CRACKED THROUGH AND INTO THE UPPER END OF THE (EXHAUST) PIPE ITSELF, WITH THE CRACK TRAVELLING ALMOST HALFWAY AROUND THE PIPE.   SUBMITTER REGULARLY FINDS THESE RISERS CRACKED AND SUSPECTS THAT A SHARP/ROUGH EDGE ON THE FLANGE CONTRIBUTES TO ITS FAILURE.    THOROUGH INSPECTION OF THIS TYPE OF EXHAUST SYSTEM AT EVERY 50-HOUR INTERVAL IS RECOMMENDED BY THE SUBMITTER. EXHAUST STAINING AROUND THE TOP OF THE PIPE IS USUALLY APPARENT. PRESSURE-TESTING OF THE WHOLE SYSTEM WHILE CARRYING OUT A.D. CF90-03R2 WILL ALSO FIND THESE DEFECTS. (TC# 20061018001)                                                                                                                                          1H71 3O3  ONT3A12    E274    5  NP910     
20061205003022006120500302SW  2006       12         5          CA061018002      120061014G6210407015001117    BLADE                                   BELL  407   407         1182206SW  ALLSN 250C  250C47B          GL                              MAIN ROTOR      DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3940                                                           (CAN) UPON POST FLIGHT INSPECTION, A TEAR AND PROTRUTION OF THE LOWER SKIN, JUST AFT OF THE LEADING EDGE OUTBOARD ERROSION STRIP WAS DISCOVERED APPROXIMATELY 4 INCHES INBOARD FROM THE TIP OF THE BLADE AT STATION 206. (TC# 20061018002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3U3  UO H2SW    E1GL                 
20061211003142006121100314NE  2006       12         11         CA061018003      120061010G6220641026005104    ROD             SKRSKY                  SKRSKYS64   S64E        8142604NE  PWA   JFTD12JFTD12A4A   52047NE                              DAMPER PISTON   BROKEN          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       3464 827   106                                                 (CAN) THE AIRCRAFT WAS INVOLVED IN AERIAL LOGGING OPERATIONS AND HAD JUST SHUT DOWN FOR ITS MIDDAY MAINTENANCE. THIS MAINTENANCE INVOLVES A FLUID LEVELS CHECK, SERVICING AND INSPECTION OF CRITICAL AREAS ON THE AIRCRAFT. ON THIS PARTICULAR DAY THE MAIN ROTOR DAMPERS WERE BEING CHECKED FOR PROPER OPERATION AND ASSOCIATED LINKAGE WEAR. THIS IS ACCOMPLISHED BY SWEEPING THE CORRESPONDING MAIN ROTOR BLADE BACK AND FORTH AT THE TIP END TO EXTEND AND RETRACT THE DAMPER PISTON AND ROD. WHEN THE AME CAME TO CHECK THE SUBJECT DAMPER HE DISCOVERED THE BLADE MOVED BACK AND FORTH FREELY WITH NO RESISTANCE FROM THE DAMPER. A CLOSER INSPECTION OF THE DAMPER BY A SECOND AME WHILE THE BLADE WAS BEING MOVED REVEALED THE DAMPER P2G72 4U4  U  H4EA    E15EA                
20061211003162006121100316EA  2006       12         11         CA061018004      220061007G8530RBLW12967EC     CYLINDER HEAD                           RKWELL700   700         7630520SW  LYC   O540  TIO540R2AD  41532EA  HARTZLHCE3Y HCE3YR2A    GL  ENGINE          BROKEN          W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         RK PARTIAL RPM/PWR LOSS      FLUID LOSS                                          CLCLIMB          1                      CA            428                           RL352361A                   (CAN) AFTER CLIMB OUT THE LT ENGINE LOST POWER AND A LOUD BANG WAS HEARD. THE ENGINE (PROPELLER) WAS FEATHERED AND THE AIRCRAFT RETURNED TO THE AIRPORT WITHOUT INCIDENT. UPON INSPECTION IT WAS FOUND THAT THE NR 2 CYLINDER ASSEMBLY WAS CRACKED/BROKEN BETWEEN THE HEAD AND BARREL. THIS ALLOWED THE HEAD TO MISALIGN AND ALLOWED THE PUSH ROD TUBES TO LEAK OIL ONTO THE TOP COWL. THE CYLINDER WAS REMOVED AND AN OVERHAUL ASSEMBLY INSTALLED. THE ADJACENT CYLINDER WAS INSPECTED AND FOUND SERVICEABLE, OIL AND SCREWS WERE INSPECTED SERVICEABLE. THE ENGINE WAS GROUND RUN AND CHECKED SERVICEABLE.  (TC NR 20061018004)                                                                                                               1L72 3O3  O  A12SW   E14EA   5  CP33EA    
20061211003182006121100318NM  2006       12         11         CA061018005      120060919G3213MS2877A344      SEAL                                    BOEING737   737*               NM  PWA   JT8   JT8D17      52049NE                              STRUT           TORN            W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA            1732                                                      (CAN) ON CLIMB OUT, NOSE GEAR RED WARNING LIGHT STAYED ON; GEAR CYCLED TWICE, NIL CURE. AIRCRAFT PROCEEDED TO AIRPORT, LANDING WAS NORMAL. ON GROUND, NOSE GEAR SERVICED, SUBSEQUENT TAKEOFF NORMAL. ON RETURN TO BASE, ONE SEAL FOUND TORN, ALL SEALS REPLACED, FULL NOSE GEAR SERVICING CARRIED OUT.  (TC NR 20061018005)                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA16WE   E2EA                 
20061211003192006121100319    2006       12         11         CA061018006      120061006G5711                SPAR                                    ARONCA7A    LSA7AC                 CONT  A65   A658        17003SO  SNSNCH72C   72CK        EA  LT WING         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2452                                                           (CAN) CRACKING AT REINFORCING PLATES.  PREVIOUS DAMAGE AT TIP. HAD PREVIOUS REPAIR. REPLACED BOTH FRONT AND REAR SPARS. (TC NR 20061018006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1H71 3O3  O  A759    E205    5  NP9045    
20070108001872007010800187SO  2007       1          8          CA061018007      220061011G8520                PISTON                                  AMTR  CUBY  CUBYACROTNER05624DPGL  CONT  O200  O200*       17020SO                              NR1 CYLINDER    CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1100                                                           (CAN) ENGINE WAS TORN DOWN FOR INSPECTION DUE TO SMALL AMOUNT NON FERROS METAL IN FILTER.  ENGINE TIME 2,707 HOUR. FRONT BEARING SLIGHT WEAR AND FLAKING (NORMAL FOR HIGH TIME ENGINE).   NR 1 PISTON SKIRT CRACKED AT 1,100 HOURS.   NOTE: THIS IS THE 4TH PISTON THAT I HAVE SEEN. RANGING FROM 1,100 HOURS TO 2,100 HOURS.  ACTION ON ENGINE - PISTON REPLACED NEW MAIN BEARINGS INSTALLED.  (TC NR 20061018007)                                                                                                                                                                                                                                                                                                                             1H71 3O3  ONCEXPA1H71E252                 
20070613001222007061300122    2007       6          13         CA061018008      420061011G6113SB10401         SPINNER                                 FRCHLDSA227 SA227CC     3377522SW  GARRTTTPE331TPE33111U   01514WP  MCAULY4HFR344HFR34C652  NE  LT PROPELLER    DENTED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) GOOSE HIT THE OB SIDE OF THE LT PROP SPINNER.  DAMAGE WAS MINIMAL TO THE SPINNER WHERE THE BLADE CUT OUT IS.  THERE WAS ALSO MINIMAL DAMAGE TO THE CHIN COWL PN 27-63026-053.  DAMAGE ON BOTH UNITS WERE COVERED BY THE SRM LIMITS OF .3750 DEGREES 4. (TC NR 20061018008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4T4  TRTA18SW   E4WE    6  C3PNE     
20070507000952007050700095SW  2007       5          7          CA061018009      120061005G29102781032005      LINE                                    FRCHLDSA227 SA227CC     3377522SW  GARRTTTPE331TPE33111U   01514WP  MCAULY4HFR344HFR34C652  NE  HYD SYSTEM      CRACKED         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) HYD FLUID WAS DISCOVERED FROM GEAR UP LINE WHEN SYSTEM PRESSURE WAS APPLIED.  LINE WOULD ONLY LEAK AFTER 1200 PSI WAS APPLIED, SYSTEM PRESSURE WAS 2000 PSI.  PIN HOLE WAS IN RADIUS OF LINE. (TC NR 20061018009)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4T4  TRTA18SW   E4WE    6  C3PNE     
20070507000962007050700096SW  2007       5          7          CA061018010      120060920G2913PV304426        PUMP                                    FRCHLDSA227 SA227CC     3377522SW  GARRTTTPE331TPE33111U   01514WP  MCAULY4HFR344HFR34C652  NE  HYD SYSTEM      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) UPON ROUTINE SPLINE REPLACEMENT IT WAS NOTICED THAT A CASTING DEFECT HAD BEEN FOUND AT THE BASE OF THE PUMP BELOW A FITTING.  THE NATURE OF THE CASTING DEFECT IS WHAT IS TERMED AS A COLD SHUNT.  A FLOURSECENT PENETRANT INSPECTION WAS CARRIED OUT AND THE COLD SHUNT WAS NOT FUSED CREATING A FATIQUE CRACK SINCE THE PUMP HAD BEEN IN SERVICE FOR SOME TIME.  PUMP WAS REJECTED. (TC NR 20061018010)                                                                                                                                                                                                                                                                                                                                 2L72 4T4  TRTA18SW   E4WE    6  C3PNE     
20070808001172007080800117SW  2007       8          8          CA061018011      120061018G76033219012123      CABLE                                   SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE33111U   01514WP  MCAULY4HFR344HFR34C652  NE  POWER LEVER     BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) RT POWER LEVER CABLE WAS DISCOVERED BROKEN 1 FOOT FROM POWER LEVER ATTACH POINT (TC NR 20061018011).                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4T4  TRTA8SW    E4WE    6  C3PNE     
20070808001182007080800118SW  2007       8          8          CA061018012      120061015G561092063H0421      WINDSHIELD                              SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE33111U   01514WP  MCAULY4HFR344HFR34C652  NE  COCKPIT         FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) AIRCRAFT WAS IN CRUISE FLIGHT WHEN THE RT WINDSHIELD SHATTERED, OUTER PANE.  THE ELT WENT OFF AND HAD TO BE RESET AT THE SAME TIME.  REPORTS OF ARCING ON INSIDE OF WINDSHIELD FROM (P) STATIC BEFORE OUTER PANE CRACKED. (TC NR 20061018012)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4T4  TRTA8SW    E4WE    6  C3PNE     
20061205002602006120500260NM  2006       12         5          CA061018013      120061018G5315147A550412      FLOORBEAM                               BOEING737   737790      13844CNNM                                                               BS 947          CORRODED        W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) FLOORBEAM CORRODED AT BS 947.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F    RTA16WE                        
20061211003202006121100320    2006       12         11         CA061018014      420060915G6122                GOVERNOR                                CESSNA206   U206G       2073356CE  CONT  O520  IO520F      17032SO  MCAULYD3A34 D3A34C404   GL  ENGINE          MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 XJ ENGINE FLAMEOUT           WARNING INDICATION                                  CRCRUISE         1                      CA                                          1686209F                    (CAN) PROPELLER GOVERNOR FAILED IN FLIGHT CAUSING SEVERE OVERSPEED OF ENGINE. UPON LANDING, THE ENGINE OIL SCREEN WAS FOUND TO BE METAL CONTAMINATED. PROPELLER GOVERNOR WAS REMOVED AND METAL WAS DISCOVERED AT GOVERNOR PAD. NO SCREEN WAS PRESENT BETWEEN GOVERNOR AND ENGINE. ENGINE DISMANTLED AND OIL TRANSFER COLLAR FOUND SEVERELY WORN, THE OIL PUMP WAS DAMAGED BEYOND REPAIR, THE CRANKSHAFT WAS WORN IN THE TRANSFER COLLAR AREA AND THE CRANKCASE WAS BADLY FRETTED. ONE CAMSHAFT LOBE AND ONE LIFTER FACE WERE ALSO SEVERELY WORN. INSPECTION WAS LIMITED TO VISUAL AND MEASURING. NO NON-DESTRUCTIVE TESTING WAS CARRIED OUT. (TC NR 20061018014)                                                                                1H71 3O3  O  A4CE    E5CE    5  CP47GL    
20061205003132006120500313CE  2006       12         5          CA061019002      120061013G53111014300263      FRAME                                   BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA                              BS 207          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       16144                                                          (CAN)  SPECIAL INSPECTION  50 WAS COMPLETED AS PER RAYTHEON MM 5-20-05, WHICH INVOLVES THE FOLLOWING: FRAME WEB FS 179 THROUGH FS 271  INSPECT THE FRAME WEBS FOR CRACKS FROM THE LIGHTNING HOLES AND STRINGER CUTOUTS. THE FRAMES SHOULD BE INSPECTED FROM THE LOWER CENTERLINE TO STRINGER 4. EXAMINE THE CROSSTIES CLOSELY AT STRINGER 7 POSITION. THE INSPECTION INTERVAL IS INITIALLY 10,000 CYCLES AND AT 1000 CYCLES THERE AFTER.  DURING THIS INSPECTION THE RT FUSELAGE FRAME  207.0 (P/N:101-430026-3) WAS FOUND CRACKED IN TWO LOCATIONS. THE FIRST CRACK WAS LOCATED AT THE UPPER EDGE OF THE FRAME LIGHTNING HOLE MIDPOINT OF RT STRINGER 9 AND RT STRINGER 10 (WL 103.0). THE CRACK MEASURED .900 IN LENGTH. THE SECOND CRACK WAS 1L72 4T4  T  A24CE   E4EA                 
20070129003272007012900327CE  2007       1          29         CA061019003      120061018G3220AN517A          BOLT                                    CESSNA310   310R        2074245CE  CONT  O520  IO520M      17032SO  MCAULY3AF32C3AF32C*     GL  NLG             SHEARED         W      O   OTHER                                                                                           O  OTHER                                                                         LDLANDING        1                      CA                                                                      (CAN) ON LANDING THE MAIN GEAR CAME DOWN AND LOCKED BUT THE NOSE GEAR STAYED UNLOCKED. THE AN5-17A BOLT CONNECTING THE DRAG LINK ASSY TO THE DRAG BRACE TRUSS ASSY. HAD FAILED CAUSING THE NOSE GEAR STRUT ASSY TO JAM AGAINST THE TRUSS ASSY HOLDING THE GEAR FROM COLLAPSING ON LANDING. (TC NR 20061019003)                                                                                                                                                                                                                                                                                                                                                                                                                                  1L72 3O3  O  3A10    E5CE    5  CP22EA    
20061211003212006121100321SW  2006       12         11         CA061019004      120061003G2844                INDICATOR                               BELL  206   206L        1181522SW  ALLSN 25OC  250C20R          GL                              FUEL PRESSURE   MALFUNCTIONED   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                  210D                                                (CAN) FUEL PRESSURE OVER-READING. PEGS AT 30 PSI WITH BOTH PUMPS AND GENERATOR ON. REMOVED FOR REPAIR AT INSTRUMENT SHOP. (TC NR 20061019004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1G71 3U3  U  H2SW    E4CE                 
20061211003232006121100323SW  2006       12         11         CA061019005      120061003G77122060751853      INDICATOR                               BELL  206   206L        1181522SW  ALLSN 25OC  250C20R          GL                              TORQUE          LEAKING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) OIL IN GAUGE GLASS. REMOVED FOR REPAIR AT INSTRUMENT SHOP. (TC NR 20061019005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1G71 3U3  U  H2SW    E4CE                 
20061205002682006120500268EA  2006       12         5          CA061019007      120061018G61238190026         PRESSURE SWITCH                         DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A27      52043EA  HARTZLHCB3T HCB3TN3     GL  AUTOFEATHER SYS FAILED          W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA            1439                                                      (CAN) AFTER TAKE OFF WHILE REDUCING POWER FROM TAKE OFF POWER TO CLIMB, THE L/H PROP AUTOFEATHERED. AUTO FEATHER CIRCUIT BREAKER PULLED AND PROP RETURNED TO NORMAL. MAINTENANCE CONFIRMED SNAG AND REPLACED THE AUTOFEATHER PRESSURE SWITCH, CARRIED OUT GROUND RUNS AND RETURNED THE AIRCRFAT TO SERVICE. (TC# 20061019007)                                                                                                                                                                                                                                                                                                                                                                                                                   1H72 3T4  TRTA9EA    E4EA    6  CP15EA    
20061205002762006120500276NM  2006       12         5          CA061019008      120061017G522085220281007     SEAL                                    DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF15      NE  EMERGENCY EXIT  LEAKING         W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA       4982 4982                                                      (CAN) DURING CRUISE, FLIGHT CREW REPORTED R SIDE EMERG EXIT DOOR SEAL FAILED (LEAKING) RESULTING IN PRESSURIZATION LOSS . AIRCRAFT REQUESTED AND WAS CLEARED TO A LOWER ALTITUDE. AFTER NORMAL LANDING, MAINTENANCE INSPECTED AND REPLACED EMERGENCY EXIT DOOR SEAL. (TC# 20061019008)                                                                                                                                                                                                                                                                                                                                                                                                                                                          2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20061205002732006120500273SO  2006       12         5          CA061019009      220061018G74141051324         SPRING                                  CESSNA210   T210L       2073449CE  CONT  O520  TSIO520H    17040SO  MCAULYD3A34 D3A34C402   GL  MAGNETO         BROKEN          W      O   OTHER                                                                                           R  PARTIAL RPM/PWR LOSS                                                          NRNOT REPORTED   1                      CA                  217469R                                             (CAN) NOTE THE SERIAL NUMBER ON THE ENGINE ON THIS FORM IS INCORRECT IT IS 217469-R.  THE IMPULSE COUPLING SPRING WAS FOUND BROKEN. CUSTOMER HAD COMPLAINED OF ROUGH RUNNING CHECK MAG DROP, REMOVED MAGS AND INSPECTED.  THE SPRINGS WERE BROKEN IN BOTH MAGNETOS,                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3O3  O  3A21    E8CE    5  CP47GL    
20061211003242006121100324EA  2006       12         11         CA061019011      120060806G2897CC670582071     CONDUIT                                 CNDAIRCL600 CL600*             EA  GE    CF34  CF348C1          NE                              WIRING COVER    INTERFERENCE    W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2551 2551                                                      (CAN) DURING GROUND INSPECTION NOTICED FUEL LEAK NEAR FRONT SPAR AREA IN BELLY PANEL. INSPECTION FOUND ELECTRICAL CONDUIT FOR LT FUEL BOOST PUMP, WIRE COVERING INTERFERING WITH FLARE AT BULKHEAD FITTING. THIS ALLOWED FUEL TO PASS INTO THE CONDUIT AND OUT OF BELLY. WIRING COVERING TRIMMED BACK AND CONDUIT RESECURED. (TC NR 20061019011)                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F4  FRTA21EA   EOOO63EN             
20061211003252006121100325EA  2006       12         11         CA061019012      220060821G732230804           FLOAT           PREAIR                                                     LYC   O320  O320*       41508EA                              CARBURETOR      UNSERVICEABLE   W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA            3     A1211973                                            (CAN) THE CARBURETOR WAS DISASSEMBLED INSPECTED AND THE FLOAT ASSY HAD GAS IN .5 OF THE FLOAT.  FLOAT HAD NO APPARENT HOLES OR CRACKS AS FLUID WAS INSIDE AND WOULD NOT DRAIN OUT. (TC NR 20061019012)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 3  O          E274                 
20070129003282007012900328EU  2007       1          29         CA061020001      120061018G2750527521213       FLAP                                    PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  WING            OBSTRUCTED      W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             NRNOT REPORTED   1                      CA                                                                      (CAN) ICE BUILD UP INTO THE IB FLAP COVER CAUSED THE FLAPS TO NOT GO FULL UP.  IT TRIPPED THE FLAP CIRCUIT BREAKER.  THE ICE CAUSED THE ROD TO BEND FROM THE STRESS OF TRYING TO MOVE THE FLAP UP.  IT WAS NOTICE BY SEEING A 50 AMP DRAW FROM THE FLAP MOTOR.  ROD REPLACED, ICE MELTED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20061020001)                                                                                                                                                                                                                                                                                                                                                                                                  1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20061205003012006120500301EU  2006       12         5          CA061020004      120061014G73341379287L405     LINE                                    BAG   JETSTMJETSTM3212  1500217EU  GARRTTTPE331TPE33110UG  01514WP                              LT NACELLE      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) P3 LINE FLANGE FOUND WITH SMALL CRACK DURING ROUTINE ENGINE CHANGE. LINE REPLACED WITH NEW UNIT. (TC# 20061020004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4T4  TRTBA15CAA E4WE                 
20061211003272006121100327NM  2006       12         11         CA061020005      120060815G3230483023          SEQUENCE VALVE                          BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  NLG DOOR        FAILED          W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) AFTER GEAR WAS SELECTED UP IN CLIMB OUT, NOSE GEAR DOOR CAUTION WAS ON TOGETHER WITH NOISE OF SPINNING WHEEL. QRH LANDING GEAR DOOR MALFUNCTION PERFORMED. AFTER GEAR WAS SELECTED DOWN DOOR CAUTION DISAPPEARED BUT WE NOW HAD AN INDICATION OF UNSAFE NOSE GEAR ( RED ). QRH ALTERNATE LANDING GEAR EXTENSION PERFORMED AND GREEN LIGHT FOR NOSE GEAR RECEIVED. NORMAL LANDING PERFORMED AND TAXIED TO PARKING. PASSENGERS AND CREW WAS BRIEFED SEVERAL TIMES DURING THE FLIGHT.  NLG SOLENOID SEQUENCE VALVE REPLACED IAW 32-31-71-400-801 (TC NR 20061020005)                                                                                                                                                                         2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
20061211003292006121100329NM  2006       12         11         CA061020006      120060824G3220471515          SENSOR                                  BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  NLG             FAILED          W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) AFTER TAKEOFF, LANDING GEAR DID NOT RETRACT. INDICATION SHOWED 3 GREENS AND 3 REDS. AFTER EMERGENCY CHECKLIST WAS COMPLETED THE DECISION FOR RE-LANDING WAS MADE. CABIN PAX AND STATION WERE INFORMED AND SUCCESSFUL RELANDING PERFORMED. FOUND NOSE WHEEL CENTER SENSOR FAULT AND SENSOR REPLACED. (TC NR 20061020006)                                                                                                                                                                                                                                                                                                                                                                                                                   2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
20061205002812006120500281EA  2006       12         5          CA061020007      120061017G5700                UNKNOWN                                 DHAV  DHC6  DHC6300     2802606EA                                                                               UNKNOWN         W      A   UNSCHED LANDING                                                                                 E  VIBRATION/BUFFET                                                              CRCRUISE         1                      CA                                                                      (CAN) TYPE CERTIFICATE HOLDER (TCH) RECEIVED CALL INDICATING THIS AIRCRAFT WAS IN LEVEL FLIGHT WITH AN INDICATED AIRSPEED OF 120 KNOTS. THE PILOT FELT A VIBRATION IN THE AIRFRAME, LOOKED OUT THE LT WINDOW AND SAW THAT THE LT WING WAS FLUTTERING UP AND DOWN. THE PILOT REDUCED POWER AND IMMEDIATELY RETURNED TO BASE. (TC# 20061020007)                                                                                                                                                                                                                                                                                                                                                                                                   1H72 3T    RTA9EA                         
20061205002952006120500295EA  2006       12         5          CA061022009      120061015G5610NP13932211      WINDOW                                  CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              COCKPIT         CRACKED         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) LEFT SIDE WINDOW CRACKED (NOT SHATTERED) AT FL 350 (TC# 20061022009)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F4  FRTA21EA   E15NE                
20061205002572006120500257NE  2006       12         5          CA061023002      120061019G52109220902411043   HINGE FITTING                           SKRSKYS92   S92A               NE                                                               PAX DOOR        CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       103                                                            (CAN) THE FOLLOWING INFORMATION REFERS TO CHC HELICOPTERS INTERNATIONAL GROUND OCCURRENCE REPORT ,WHICH WAS SUBMITTED BY OUR BASE IN MALAYSIA: "ON CARRYING OUT 50 HOUR INSPECTION ON PASSENGER DOOR AND HINGES, FOUND FORWARD UPPER HINGE CRACKED. CRACK WAS RUNNING FROM UPPER AFT BOLT HOLE AND DOWN ALONG HINGE FITTING". PLEASE NOTE THAT THIS PARTICULAR HINGE FITTING HAS ONLY BEEN INSTALLED SINCE AUGUST 2006. . THE PREVIOUSLY INSTALLED HINGE FITTING WAS FOUND CRACKED ON 22 AUGUST 2006 AND HAD FLOWN A TOTAL OF 168.6 HOURS (AIRCRAFT WAS UNDERGOING 50 HOURS INSPECTION. DID NOT RESULT IN ANY OTHER FAILURE. INSPECTION/MAINTENANCE WAS CONTINUED AND REPORT SUBMITTED. (TC# 20061023002)                                       2G72 4U      R00024BO                     
20061205002942006120500294EA  2006       12         5          CA061023004      120061016G3097302114BB1       WIRE                                    DHAV  DHC8  DHC8311     1386006EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF15      NE  ELECTRICAL      BURNED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            CRCRUISE         1                      CA       3371933719                                                     (CAN) DURING CRUISE , FLIGHT CREW NOTICED NR 2 ENGINE LIP HEATER INDICATION SHOWING FAILURE OF LIP HEATER, DUE TO ICING CONDITIONS AT DESTINATION AIRPORT CREW ELECTED TO RETURN TO ORIGINATING AIRPORT. NORMAL LANDING. DURING MAINTENANCE INVESTIGATION FOUND NO POWER TO LIP HEATER. PROBLEM TRACED TO BURNED WIRE 30-21-14BB-18 IN WIRING BUNDLE BEHIND LAVATORY WALL ( AFT OF CO-PILOT SEAT). WIRING BUNDLE HAD CHAFED ON LAVATORY WALL CAUSING INSULATION TO BE WORN. WIRE ( AND 3 OTHER WIRES IN SAME BUNDLE) REPAIRED. AIRCRAFT RETURNED TO SERVICE. (TC# 20061023004)                                                                                                                                                                  2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20061211003302006121100330SO  2006       12         11         CA061023005      220061012G8520643202          CASE                                    CESSNA401   401         207590CCE  CONT  O520  TSIO520E    17040SO  MCAULY3AF32C3AF32C*     GL  ENGINE          CRACKED         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA            1324                          521407                      (CAN) THE ENGINE HAD A SMALL OIL LEAK. AFTER REMOVING THE DIP STICK ASSEMBLY, A CRACK WAS FOUND BETWEEN NR 2 AND NR 4 CYLINDERS. THE ENGINE WAS REMOVED FOR OVERHAUL. (TC NR 20061023005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 3O3  O  A7CE    E8CE    5  CP22EA    
20061205002482006120500248EA  2006       12         5          CA061024001      120061023G5610601R3303314     WINDSHIELD                              CNDAIRCL600 CL6002C10   1390015EA                                                                               FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) F/O WINSHIELD BROKE WHILE AT CRUISE ALTITUDE, DIVERTED  C/A -RAR F/O WINDSHIELD IAW AMM (CRJ 700) 56-11-01 REF LGPG2160865 ITEMS 1 AND 2 FOR FUNCTIONAL CHECK AND OPERATIONAL CHECK. OPS CHECKS AND FUNCTIONAL CHECKS OK. (TC# 20061024001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F    RTA21EA                        
20061205002562006120500256EA  2006       12         5          CA061024002      220061020G8500TIGO541E1A      ENGINE                                  PIPER PA31  PA31P       7103120SO  LYC   O541  TIGO541E1A  41539EA                              RIGHT           MALFUNCTIONED   W      E   ENGINE SHUTDOWN                                                                                 MJ OVER TEMP                 WARNING INDICATION                                  CLCLIMB          1                      CA                                          RL27662                     (CAN) AFTER TAKEOFF, RT ENGINE STARTED MAKING POWER FLUCTUATIONS WITH A RAPID EGT RISE. RT ENGINE WAS SHUT DOWN IN DESCENT AND AIRCRAFT RETURNED SAFELY. A MAINTENANCE INVESTIGATION IS UNDER WAY TO DETERMINE THE CAUSE. REPORT TO FOLLOW WHEN CAUSE IS IDENTIFIED. (TC# 20061024002)                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L72 3O3  O  A8EA    E19EA                
20061205002452006120500245EU  2006       12         5          CA061024003      120061024G2120                UNKNOWN                                 BAG   JETSTMJETSTM3212  1500217EU  GARRTTTPE331TPE33110UG  01514WP  ROTOL R333  R333482F12  GL  COCKPIT         ODOR            W      A   UNSCHED LANDING                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE FLIGHT CREW COULD DETECT FUMES OF AN ELECTRICAL NATURE. AIRCRAFT RETURNED TO DEPARTURE POINT WITHOUT INCIDENT. A MAINTENANCE INVESTIGATION IS UNDER WAY TO DETERMINE THE CAUSE OF THE FUMES/ODOUR. A REPORT WILL FOLLOW WHEN CAUSE IS IDENTIFIED. (TC# 20061024003)                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4T4  TRTBA15CAA E4WE    6  CP61GL    
20061205002472006120500247EA  2006       12         5          CA061025002      120061024G352013740003        SWITCH                                  CNDAIRCL604 CL604       1900301EA  GE    CF34  CF343B1          NE                              OXYGEN CONTROL  INOPERATIVE     W      O   OTHER                                                                                           G  MULTIPLE FAILURE                                                              NRNOT REPORTED   1                      CA       1656                                                           (CAN) WHILE CARRYING OUT A 12 MONTH CABIN OXYGEN FUNCTIONAL TEST, FOUND THE OXYGEN CONTROL PANEL SEMI-FUNCTIONAL. THE ROTARY KNOB WOULD NOT GO TO THE "CLOSED" POSITION WITHOUT EXCESSIVE FORCE. ROTATING TO THE "OVERRIDE" POSITION FUNCTIONED PROPERLY BUT OXYGEN FLOW TO THE CABIN MASKS SEEMED RESTRICTED. SELECTING THE "THERAPEUTIC" SWITCH "ON" WAS EXTREMELY STIFF AND WOULD NOT TURN OFF WHEN SELECTED. FOUND PANEL TO BE CONTAMINATED. MOST LIKELY COFFEE AND/OR SOFT DRINK RESIDUE. NEW PANEL INSTALLED, FLOW TO CABIN OXYGEN MASKS SEEMED TO INCREASE TO DOUBLE THE FLOW RATE OF THE ORIGINAL. THERAPEUTIC SWITCH OPERATED AS NORMAL.412 SQUADRON OPS WILL BE CONTACTED TO APPRISE PILOTS OF THE FINDINGS. (TC# 20061025002)        2L72 4F4  FRTA21EA   E15NE                
20061205002552006120500255NM  2006       12         5          CA061025003      120061020G271082700567001     CABLE                                   DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF23      NE  RT AILERON      BROKEN          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       16203                                                          (CAN) FINDINGS DURING C-CHECK INSPECTION IN AREA WING STA 171, AFT SPAR, LT AND RT REVEALED HEAVILY CHAFED AILERON CABLES IN PULLEY AREA AT WING BS 171. ON RT SIDE THE CABLE WAS SEVERELY DAMAGED AND ONLY A PART OF ONE STRAND WAS LEFT INTACT. THE CABLE IS OF TYPE 19X7 (7 STRANDS AND WITH 19 WIRES). LAST INSPECTION PERFORMED IN 2001 (TASK 2C INTERVAL) - NO FINDINGS. ON LT SIDE APPROX 40% OF THE STRANDS/WIRES WAS BROKEN. THE PULLEYS ARE MADE OF STEEL WITH A ROLLER BEARING AND UNDERNEATH THE PULLEYS IS A CABLE GUARD. CABLE TENSION APPROX 52 LBS (AMM) INSPECTION OF A NUMBER OF PULLEYS, AILERON AND SPOILER, REVEALED HEAVY WEAR/INDENTATION AT ONE SPOT AS IF THE PULLEY HAD BEEN. (TC# 20061025003)                       2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20061205002532006120500253GL  2006       12         5          CA061025004      320061022G6110                STUD            MCAULY                  CESSNA185   185F        2072820CE  CONT  O520  IO520D      17032SO  MCAULYD3A34 D3A34C403   GL  PROPELLER       UNSERVICEABLE   W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA            306   7710359                                             (CAN) WHILE INSTALLING THE MCCAULEY MODEL D3A34C403-B PROPELLER ONTO A CESSNA 185, THE ENGINEER WAS TIGHTENING THE FIBER LOCK NUTS ONTO THE PROPELLER MOUNTING STUDS, WHEN ONE OF THE NUTS KEPT ON TURNING AND DID NOT SEEM TO BE GETTING ANY TIGHTER. HE TRIED ANOTHER NEW LOCK NUT BUT THE SAME THING HAPPENED AND THEN NOTICED THAT THE MOUNTING STUD WAS BEING PULLED OUT FROM THE PROP HUB. THE LOCK NUT HAD NOT BEEN TIGHTENED UP TO THE RECOMMENDED TORQUE VALUE FOR MOUNTING THE PROP BEFORE THIS STARTED TO HAPPEN. THE PROPELLER BEING INSTALLED HAD ONLY 305.7 TSO. IT WAS SENT BACK TO THE SHOP THAT OVERHAULED IT. (TC# 20061025004)                                                                                               1H71 3O3  O  3A24    E5CE    5  CP47GL    
20061211003332006121100333SW  2006       12         11         CA061025005      120060907G28221C27            CARTRIDGE                               BELL  206   206B        1181511SW  ALLSN 250C  250C20      03013GL                              BOOST PUMP      INTERMITTENT    W      O   OTHER                                                                                           J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) ABOVE 7000 FEET BOOST PUMP LIGHT WOULD COME ON. BELOW 7000 FEET WARNING LIGHT WOULS EXTINGUISH. BOOST PUMP CARTRIDGE P/N 1C27 REPLACED. (TC NR 20061025005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1G71 3U3  U  H2SW    E4CE                 
20061211003352006121100335CE  2006       12         11         CA061025006      120060502G5711                SPAR                                    BEECH 95    E95         1153410CE  LYC   O360  IO360B1B    41514EA  HARTZLHCC2Y HCC2YK2     GL  LT WING         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       7004                                                           (CAN) DUING INSPECTION IAW FAA AD 90-08-14 AND SB53-2269 REV 2 SHORT CRACKS WERE VISUALLY FOUND EMINATING FROM 2 HUCK BOLT LOCATIONS ON THE LT FORWARD WING SPAR CARRY THROUGH WEB FACE. CRACKS WERE CONFIRMED BY LPI. REPAIRED IAW MFG FAA APPROVED DRAWING 58-40009 AND 58-4008 REV C FORWARD LT FACE ONLY. (TC NR 20061025006)                                                                                                                                                                                                                                                                                                                                                                                                               1L72 3O3  O  3A16    1E10    5  CP920     
20070129003292007012900329CE  2007       1          29         CA061025007      120060930G6123                CONTROL CABLE                           BEECH 95    E95         1153410CE  LYC   O360  IO360B1B    41514EA  HARTZLHCC2Y HCC2YK2     GL  RT PROP         DEFECTIVE       W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             CRCRUISE         1                      CA                                                                      (CAN) AFTER A ROUTINE TRAINING FLIGHT THE PILOT REPORTED THAT THE RT PROP CONTROL WAS VERY STIFF AND SPRINGY AND THE PROP WAS SLOW TO FEATHER. THE CONTROL WAS DISCONNECTED FROM THE GOVERNOR AND THE DEFECT WAS CONFIRMED TO BE THE CONTROL CABLE. THE TTSN FOR THE ENGINE CONTROL CABLES WERE UNKNOWN. ALL LT AND RT ENGINE CONTROL CABLES WERE REPLACED WITH NEW CONTROLS. (TC NR 20061025007)                                                                                                                                                                                                                                                                                                                                               1L72 3O3  O  3A16    1E10    5  CP920     
20061205002412006120500241NM  2006       12         5          CA061026001      120061025G49104503067A        APU                                     BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                                              MALFUNCTIONED   W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      ININSP/MAINT     1                      CA                                                                      (CAN) APU ENCLOSURE SUFFERED STRUCTURAL DAMAGE AFTER FUEL VAPOR IGNITED.  CREW HAD TRIED TO START APU AFTER LANDING MINIMUM TWICE, UNABLE TO START. NOT POSSIBLE TO GET FAULT CODES SO MECHANIC CALLED. MECH STARTED APU AND THEN IT AUTO SHUTDOWN. MECH STARTED APU AGAIN AND SAME RESULT. MECH OBSERVED FUEL VAPOR FROM EXHAUST BUT NOT FROM FUEL DRAIN. MECH PULLED CIRCUIT BREAKER FOR FUEL SOLENOID IN ORDER TO PERFORM DRY CRANK TO VENT APU. WHEN PUSHING POWER SWITCH THERE WAS AN EXPLOSION IN THE APU BAY.  DAMAGE TO THE APU ENCLOSURE AND DOORS OCCURRED. TAIL CONE TO BE REPLACED. (TC# 20061026001)                                                                                                                               2H72 4T4  TRTA13NM   E00062EN             
20061205002312006120500231NM  2006       12         5          CA061026002      120061026G2710FL4C62          BEARING                                 DHAV  DHC8  DHC8102     2809003NM                                                               AILERON CONTROL JAMMED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING THE C CHECK INSPECTION, NR 5 BEARING ON 8 IN A WING AILERONS SYSTEME CABLE FAIRLEADS WAS FOUND JAMMED AND FLAT SPOTTED. ALL CABLES PASSING THRU THE FAIRLEAD HAVE TO BE REPLACE DUE TO THE CHAFFING IN THE BEARING, THE WORSE ONE WAS THE CABLE P/N:82700519-001. THE PART NUMBER IN THE IPC WAS FL4C6-2 BUT THE NUMBER ON THE BEARING WAS P15SP1 WITH THE WORD SARMA STAMP ON IT. (TC# 20061026002)                                                                                                                                                                                                                                                                                                                               2H72 4T    RTA13NM                        
20061205002402006120500240CE  2006       12         5          CA061026003      120061025G324650060285        WHEEL                                   BEECH 1900  1900C       1154161CE  PWA   PT6   PT6A65B     52043EA                              MLG             DEPARTED        W      K   NONE                                                                                            D  INFLIGHT SEPARATION                                                           ININSP/MAINT     1                      CA                                                                      (CAN) PILOTS DISCOVERED NR 4 WHEEL ASSY MISSING AFTER ARRIVING AT DESTINATION. PASSENGER SAID A BANG WAS HEARD DURING TAKE-OFF. MAINTENANCE PERSONNEL DISPATCHED TO INSPECT AIRCRAFT,  AND IF INSPECTED SERVICEABLE INSTALL NEW WHEEL ASSY AND RETURN TO BASE. AIRCRAFT INSPECTED SERVICEABLE, M/W INSTALLED AND AIRCRAFT FLOWN TO BASE. O/B BEARING APPEARS TO HAVE FAILED. (TC# 20061026003)                                                                                                                                                                                                                                                                                                                                                  2L72 4T4  TRTA24CE   E4EA                 
20061205002352006120500235EU  2006       12         5          CA061026004      120061026G3411                INDICATOR                               GIPPLDGA8   GA8         3900102EU  LYC   O540  IO540K1A5   41532EA                              PITOT HEAT      BURNED          W      O   OTHER                                                                                           BH SMOKE/FUMES/ODORS/SPARKS  ELECT. POWER LOSS-50 PC                             NRNOT REPORTED   1                      CA       1100                                                           (CAN) PILOT REPORTED MALFUNCTION OF PITOT HEAT BREAKER SWITCH, UPON INSPECTION, CIRCUIT BOARD ATTACHED TO BACK OF SWITCH WAS FOUND BADLY BURNT AND END OF WIRE CONNECTION FROM THE PITOT TO THE POWER SWITCH WAS FOUND OVERHEATED.  MAIN PITOT WAS REPAIRED.  THE CIRCUIT BOARD CLAMPED BETWEEN THE BREAKER SWITCH AND THE PITOT HEAT WIRE WAS U/S DUE TO OVERHEAT.  THIS INSTALLATION APPEARS TO BE FROM FACTORY.  2 POSSIBLE CAUSES OF THIS FAILURE: 1) FIBERGLASS CIRCUIT BOARD COULD NOT STAND UP TO PRESSURE OF ATTACHMENT SCREW.  DUE TO POOR CONNECTION , THE CONNECTION WOULD HAVE HEATED UP AND UPON GETTING HOT ENOUGH, RESIN IN FIBERGLASS BOARD WOULD HAVE DISINTIGRATED CAUSING PITOT HEAT FAILURE. 2) PRINTED CIRCUIT BOARD HAS WI1H71 3O3  ONT        1E4                  
20061205002922006120500292WP  2006       12         5          CA061026005      120061016G7600                SUPPORT                                 GRUMANTS2   TS2ACALFORST3951102WP                                                               ENG CONTROLS    UNSERVICEABLE   W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                  NA                                                  (CAN) IN SOME CASES, THE WELD BRAZING THAT CONNECTS THE TELEFLEX CONTROL SUPPORT BEARINGS TO THE ENGINE CONTROL QUADRANT ASSEMBLY HAVE BEEN FOUND TO BE CRACKED OR HAVE INSUFFICIENT BONDING TO THE BEARING SUPPORT PLATE. THIS PROBLEM, IN ADDITION TO INTERNAL WEAR IN THE BEARINGS, CAN CAUSE ADDITIONAL STRESS TO THE REMAINING BRAZED WELD. IN EXTREME CASES THE BEARING CAN SEPARATE FROM THE BEARING SUPPORT PLATE AND CAUSE UNEXPECTED POWERPLANT SETTINGS.  ORIGINALLY DISCOVERED IN AUGUST 2002 - CASCADE AEROSPACE ISSUED A SERVICE BULLETIN (SB 3127-001) TO INSPECT THE ENTIRE FLEET WITHIN SEVEN DAYS OR 60 FLIGHT HOURS (WHICHEVER CAME FIRST). RECURRING NDT INSPECTIONS WERE SCHEDULED EVERY 400 HOURS TAT OR DURING AN ANNUAL 2H72 4R      A25WE                        
20070129001292007012900129CE  2007       1          29         CA061027001      120061023G27200510105338      CONTROL CABLE                           CESSNA172   172M        2072418CE  LYC   O320  O320E2D     41508EA  MCAULY1C160 1C160DTM    GL  RUDDER SYSTEM   MISROUTED       W      K   NONE                                                                                            WF INADEQUATE Q C            FLT CONT AFFECTED                                   ININSP/MAINT     1                      CA       6326 6326                                                      (CAN) WHILE CARRYING OUT A 100 HOUR INSPECTION IT WAS DISCOVERED THAT WHEN TENSION WAS PLACED ON THE RT RUDDER PEDAL, IT WAS RUBBING AGAINST THE RT AILERON DIRECT CABLE PULLEY CLEVIS PULLEY GUARD IN THE FORWARD TUNNEL SECTION OF THE FUSELAGE. THE RUBBING WAS SUFFICIENT ENOUGH TO CAUSE  6 WIRES TO BREAK. THE CABLE WAS IMPROPERLY ROUTED OVER THE AILERON DIRECT PULLEY CLEVIS PIN CABLE GUARD AND SHOULD HAVE PASSED UNDERNEATH. THE CABLE WAS FRAYED APPROXIMATELY 7 INCH AFT OF THE ATTACHMENT TO THE AFT RUDDER BAR. THE FRAYED WIRE CAN ONLY BE SEEN BY REMOVAL OF THE PLASTIC CENTER CONSOLE AND VIEWED THROUGH THE TUNNEL SECTION WITH AN INSPECTION MIRROR AND TENSION APPLIED TO THE RT RUDDER. NO RECORD OF THE CABLE EVER BEI1H71 3O3  ONT3A12    E274    5  NP910     
20061205002502006120500250SW  2006       12         5          CA061027002      120061023G553141000823        SPAR            AEROCD                  GULSTM690TP 690A        0141722SW  GARRTTTPE331TPE3315     01514WP                              VERTICAL STAB   CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       8830                                                           (CAN) DURING ANNUAL X-RAY INSPECTION OF THE VERTICAL STABILIZER, A CRACK WAS DETECTED ON THE LEFT HAND SIDE OF THE VERTICAL STABILIZER CENTRE SPAR AT THE 4TH FASTENER ABOVE THE DOUBLER. THE CRACK APPEARS TO RUN INTO THE RADIUS OF THE CENTRE SPAR. THE AIRCRAFT WILL BE REPAIRED PRIOR TO BEING RELEASED BACK INTO SERVICE. (TC# 20061027002)                                                                                                                                                                                                                                                                                                                                                                                               1H72 3T4  T  2A4     E4WE                 
20061205003002006120500300SW  2006       12         5          CA061027003      120061014G771231017263        TORQUE SENSOR                           SWRNGNSA226 SA226TC     8780404SW                                                               RT ENGINE       DAMAGED         W      E   ENGINE SHUTDOWN                                                                                 N  FALSE WARNING                                                                 TXTAXI/GRND HDL  1                      CA            4015                                                      (CAN) UPON TAXI INTO AIRPORT, THE RT ENGINE SHUT DOWN DUE TO THE CENTER GEAR ON THE TORQUE SENSOR SHAFT & WHERE NUT HOLDS THE GEAR ON BROKE OFF. AT THIS TIME THE A/C WAS AT THE TERMINAL AND NO PROBLEMS AROSE DUE TO THIS INCIDENT. SUSPECT THE NUT ON THE SHAFT WAS OVERTORQUED AT OVERHAUL BY A APPROVED OUTSIDE FACILITY. THE R/H ENGINE WAS REPLACED AND THE ENGINE P-54108 WAS FORWARDED TO THE ENGINE SHOP FOR REPAIR. (TC# 20061027003)                                                                                                                                                                                                                                                                                                2L72 4T    RTA8SW                         
20061205002542006120500254NE  2006       12         5          CA061027004      220061021G73221897001161      SHAFT           BEECH                   BEECH 18    D18S        1151004CE  PWA   R985  R985AN14B   52008NE                              AIR VALVE       WORN            W      D   RETURN TO BLOCK                                                                                 F  FLT CONT AFFECTED                                                             TXTAXI/GRND HDL  1                      CA       5598                                                           (CAN) PRIOR TO STARTUP, PILOTS` FOUND THE LH MANIFOLD HEAT CONTROL JAMMED.  FURTHER INVESTIGATION DISCOVERED ONE OF THE SCREWS SECURING THE AIR VALVE PLATE TO THE AIR VALVE SHAFT HAD DEPARTED, AND THE OTHER SCREWS WERE VERY LOOSE.  WRONG TYPE OF NUT WAS USED ON THE SCREWS, CONTRIBUTING TO THE LOOSE HARDWARE.  PARTS MANUAL REQUIRES AN365-832 TYPE NUTS, WHILE PRESSED STEEL TYPE OF NUT WAS FOUND INSTALLED IN BOTH AIRBOXES.  VALVE WAS REPAIRED AND AIRCRAFT RETURNED TO SERVICE.  THIS HAD THE POTENTIAL TO BE AN ENGINE FAILURE. (TC# 20061027004)                                                                                                                                                                                1L72 3R3  R  A765    5E1                  
20061205002872006120500287NM  2006       12         5          CA061029001      120061017G5753654952921       BELLCRANK                               BOEING737   737201      1384454NM  PWA   JT8   JT8D9A      52048NE                              NR 2 FLAP TRACK BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) NR 2 AFT FLAP BELLCRANK WAS FOUND BROKEN WHILE ACCOMPLISHING DAILY CHECK. INVESTIGATION FOUND EXCESSIVE WEAR ON THE NR 2 AFT FLAP BELLCRANK CAM TRACK WHICH RESULTED IN THE BELLCRANK POPPING OUT OF THE CAM TRACK. UPON REPLACEMENT OF THE CAM TRACK, IT WAS DETERMINED THE CAM TRACK WAS NOT INSTALLED IAW BOEING MAINTENANCE MANUAL. THE MM REQUIRES INSTALLATION OF A TAPER SHIM TO PROPER ALIGN TRACK SO THAT THE BELLCRANK CAM ROLLER WILL RIDE PROPERLY IN THE CAM TRACK. WE BELIEVE THE BELLCRANK BROKE AFTER IT POPPED OUT OF THE CAM TRACK AND JAMMED WHEN THE FLIGHT CREW MOVED THE FLAPS.  A FLEET CAMPAIGN FOUND 2 OTHER CAM TRACKS WITH SIMULAR WEAR AND WERE ALSO MISSING REQUIRED TAPER SHIM. THE CAM TRACKS WERE REPLACED2L72 4F4  F  A16WE   E2EA                 
20061205002082006120500208EU  2006       12         5          CA061030001      120061028G2910316Q2277        LINE                                    BRAERO748   HS7482A     4231001EU  RROYCEDART  DART5342         EU                              HYDRAULIC RETURNFRACTURED       W      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) WHILE EN-ROUTE THE HYDRAULIC FLOW LIGHTS ILLUMINATED AND THE HYDRAULIC PRESSURE DROPPED TO 1900PSI. THE AIRCRAFT DIVERTED, WHERE AN UNEVENTFUL LANDING WAS MADE. MAINTENANCE INVESTIGATION REVEALED THAT THE HYDRAULIC RETURN LINE BETWEEN THE HYDRAULIC CUT OUT VALVE AND THE HYDRAULIC RESERVOIR HAD FRACTURED AT THE RESERVOIR CONNECTION. THE LINE WAS REPLACED AND THE SYSTEM TESTED SERVICEABLE. AN OPTIONAL MOD (S/B 29/44, MOD 7297) RAISED BY BAE IN 1986 REPLACED THIS RIGID LINE WITH A FLEXIBLE LINE TO PRECLUDE THIS TYPE OF FAILURE. THE LINE IN QUESTION WAS A PRE-MOD ITEM. (TC# 20061030001)                                                                                                                             2L72 3T4  T  A24EU   A196                 
20061211003372006121100337WP  2006       12         11         CA061030002      120061010G6510C0411           BEARING                                 ROBSINR44   R44         7640120WP  LYC   O540  O540F1B5    41532EA                              DAMPER          DAMAGED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       197                                                            (CAN) ABNORMAL SOUND HEARD ON SHUTDOWN.  ON FURTHER INSPECTION THE INNER RACE OF THE DAMPER BEARING ON THE TAIL ROTOR DRIVESHAFT HAD BEEN FOUND TO HAVE SPUN.  THE INNER RACE OF THE BEARING IS NOT ALLOWED ANY MOVEMENT RELATIVE TO THE DRIVE SHAFT.  THE TAIL ROTOR DRIVE SHAFT ASSEMBLY WAS REPLACED WITH A SERVICEABLE UNIT. (TC NR 20061030002)                                                                                                                                                                                                                                                                                                                                                                                            1G71 3O3  O  H11NM   E295                 
20061211003392006121100339CE  2006       12         11         CA061030003      120060627G8011631847          GEAR            CONT                    CESSNA421   421         2076010CE  CONT  O520  GTSIO520H   17032SO                              STARTER SHAFT   BROKEN          W      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  NRNOT REPORTED   1                      CA       5                                                              (CAN) (1)GEAR TOOTH BROKE OFF THE STARTER SHAFT GEAR IN A NEW STARTER ADAPTER ASSEMBLY CAUSING FOREIGN MATERIAL TO ENTER THE ENGINE LEADING TO FURTHER DAMAGE INSIDE THE CRANKCASE. FINAL RESULT WAS LOSS OF POWER TO THE RT ENGINE AND UNSCHEDULED LANDING. (TC NR 20061030003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L72 3O3  ORTA7CE    E7CE                 
20061211003402006121100340    2006       12         11         CA061030004      420061006G3422568195301       SPRING          JET                                                                                                                     VERTICAL GYRO   FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA            4681  1367M                                               (CAN) AT PREVIOUS REPAIR UNIT WAS ASSEMBLED WITH A SHOP FABRICATED PRELOAD SPRING OF LARGED DIAMETER AND HIGHER PRESSURE RATE PRELOAD SPRING SHOULD HAVE BEEN REMOVED WHEN MOD 5 INCORPORATED (TC NR 20061030004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         
20070126003032007012600303CE  2007       1          26         CA061030005      120061023G325005430223        ARM                                     CESSNA150   152         2071835CE  LYC   O235  O235L2C     41505EA  MCAULY1A103 1A103TCM    GL  NLG STEERING    BENT            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       9448                                                           (CAN)   DURING INSPECTION OF STERRING SYSTEM LT STEERING ARM TUBE FOUND BENT ON THE TUBE ASSY.   NEW PART ORDERED AND INSTALLED.  (TC NR 20061030005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1H71 3O3  ONT3A19    E223    5  NP50GL    
20061205002102006120500210SO  2006       12         5          CA061030006      120061027G7120                MOUNT                                   PIPER PA31T PA31T       7103124SO  PWA   PT6   PT6A28           EA                              ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       8215 3512                                                      (CAN) THE TOP ENGINE MOUNT PAD, LOCATED ON THE GAS GENERATOR CASE, HAD A CRACK ON THE WELD LINE APPROX. 1.75 INCHES LONG. (TC# 20061030006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L72 3T4  T  A8EA    E4EA                 
20061211003412006121100341EU  2006       12         11         CA061030007      120060518G6220350A37116220    RETAINER                                SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1        NE                              DROOP STOP      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) ON THE DAILY CHECK BY THE ENGINEER THE MAIN ROTOR BLADE DROOP STOP RING RETAINER WAS FOUND CRACKED BELOW THE RETAINER CLAMP.  NO FURTHER DAMAGE.   (TC NR 20061030007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1G71 3U3  U  H9EU    E19EU                
20061205002032006120500203NM  2006       12         5          CA061031001      120061030G324082920010147     TUBE                                    DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  MLG             LEAKING         W      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB OUT CREW REPORTED LOSS OF HYDRAULIC FLUID (DOWN 1/2 QUART). FLIGHT RETURNED TO DEPARTING AIRPORT. ALL SYSTEMS WERE OPERATING NORMALLY UNTILL LANDING ROLLOUT, AT WHICH TIME CREW REPORTED NIL BRAKES. AIRCRAFT STOPPED WITH EMERGENCY BRAKE AND WAS TOWED TO RAMP AREA WITHOUT FURTHER INCIDENT. ERS WAS REQUESTED FOR ARRIVAL BUT AN EMERGENCY WAS NOT DECLARED. NO ADVERSE PASSENGER REACTION WAS NOTED. MAINTENANCE TROUBLESHOOTING FOUND THE NR 1 SYSTEM PRESSURE LINE (IPC REF. 32-42-00 FIG. 5 ITEM - 160) TO THE LT BRAKE CONTROL VALVE TO HAVE A PIN HOLE AT THE LOWER FORWARD ELBOW. REPLACED WITH A TEMPORARY FLEX LINE. SYSTEM LEAK AND FUNCTION CHECKED SERVICEABLE. AIRCRAFT AFTT-41155:50 HOURS, CYCLES-41543. 2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20061205002092006120500209GL  2006       12         5          CA061031002      320061027G611405503214        BULKHEAD                                CESSNA172   172N        2072434CE  LYC   O320  O320D2J     41508EA  MCAULY1C160 1C160DTM    GL  SPINNER         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       77                                                             (CAN) BULKHEAD WAS INSTALLED IAW CESSNA SK172-156A INSTRUCTIONS. BULKHEAD HAS CRACKS CURVING AROUND BOLT HOLES ABOUT HALF INCH AWAY FROM THE HOLE EDGE AT THE INNER BEND RADIUS.  NOTE: THIS IS THE FOURTH OR FIFTH IDENTICALLY CRACKED BULK HEAD FOUND ON AS MANY OTHER 172 A/C IN THE PAST THREE OR SO MONTHS AT OUR FACILITY. CESSNA IS GIVING US WARRANTY FOR THE PARTS BUT NO CORRECTIVE ACTION HAS COME FORWARD AS YET. (TC# 20061031002)                                                                                                                                                                                                                                                                                                 1H71 3O3  ONT3A12    E274    5  NP910     
20061211003422006121100342SW  2006       12         11         CA061031003      120060920G6730206076031021    SERVO                                   BELL  206   206B        1181511SW  ALLSN 250C  250C20      03013GL                              ROTOR SERVO     LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       115401112                                                      (CAN) EXCESSIVE FLUID LEAKAGE.  LEAKING BEYOND LIMITS (TC NR 20061031003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1G71 3U3  U  H2SW    E4CE                 
20061205002902006120500290SO  2006       12         5          CA061031004      120061017G5344                HINGE                                   PIPER PA31  PA31350     7103110SO  LYC   O540  TIO540J2BD  41532EA                              PAX DOOR        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) CABIN LOWER ENTRANCE DOOR FORWARD HINGE LOOSE, DOOR MOVES UP AND DOWN WHEN PASSENGERS STEP ON THE LOWER DOOR STEP. FOUND THE FORWARD DOOR HINGE ATTACHMENT FRAME CRACKED AT THE ATTACHMENTS FOR THE HINGE, ALLOWING THE DOOR SILL AND CABIN FLOOR AT THE ENTRANCE TO MOVE UP AND DOWN WHEN A LOAD WAS APPLIED TO THE DOOR. FRAME REPLACED WITH NEW PART AND DOOR REINSTALLED. (TC# 20061031004)                                                                                                                                                                                                                                                                                                                                           1L72 3O3  O  A20SO   E14EA                
20061205002442006120500244EU  2006       12         5          CA061101001      120061024G2810A2824004900200  VALVE                                   AIRBUS310   A310               EU  GE    CF6   CF680C           GL                              FUEL SYSTEM     BROKEN          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) WHILE PERFORMING A GENERAL VISUAL INSPECTION INSIDE THE RIGHT HAND/OUTER FUEL TANK, THE OUTBOARD FUEL PUMP SEQUENCE VALVE WAS FOUND BROKEN. DEBRIS OF THE SEQUENCE VALVE WHERE FOUND NEARS THE RESPECTIVE FUEL PUMP CANISTER. AREA WAS CLEAN OUT. SEQUENCE VALVE ASSEMBLY REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F4  FRTA35EU   E23EA                
20061205001992006120500199EA  2006       12         5          CA061101002      120061030G5730601R1090719     CLAMP                                   CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30015NE                              ACCESS DOOR     BURNED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       25347                                                          (CAN) ELECTRICAL ARC BURN MARKS FOUND ON THE REAR FACE OF NUTPLATES (QTY 17) FOR THE WING FUEL TANK ACCESS DOORS. AS PER THE TECHNICAL RECORDS THERE WERE TWO REPORTED LIGHTNING STRIKES ON THIS AIRCRAFT SINCE  NOVEMBER 09/2005. THE BURN MARKS ARE A LIKELY INDICATION OF LIGHTNING STRIKE ENERGY PATH.  SOME OF THE ACCESS CUT-OUT ON THE UNDERWING WERE FOUND PAINTED OVER. THESE PAINT WERE REMOVED, AREA RETREATED AND NEW PANELS WERE INSTALLED. (TC# 20061101002)                                                                                                                                                                                                                                                                      2L72 4F4  FRTA21EA   E15NE                
20061205002022006120500202NE  2006       12         5          CA061101003      220061030G8530205364205523    STUD                                    CNDAIRCL215 CL2151A10   1900320EA  PWA   R2800 CA3         52026NE                              CYLINDER HOLD DOSHEARED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            1124                          P36383                      (CAN) DURING ANNUAL INSPECTION OF THE RT ENGINE 5 OF THE 15 CYLINDER HOLD DOWN STUDS ON CYLINDER NO. 2 WERE FOUND SHEARED. 3 HOLD DOWN NUTS WERE LOOSE, ALL PAL NUTS WERE INSTALLED AND TIGHT. THE PART NUMBERS FOR THE SHEARED STUDS ARE AS  FOLLOWS: 205364 (QTY 2), 205523 (QTY 2)AND 204850 (QTY 1). ADDITIONAL INSPECTIONS OF THE ENGINE WILL BE ACCOMPLISHED. ANY FURTHER FINDINGS/RESULTS WILL BE REPORTED.                                                                                                                                                                                                                                                                                                                              2H72 4R4  RRTA14EA   E231                 
20061205002052006120500205NE  2006       12         5          CA061101005      120061029G32465004410         WHEEL                                   SKRSKYS76   S76A        8143006NE                                                               MLG             CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) WHEEL CRACKED AND AUDIBLE AIR ESCAPING FOUND ON DAILY INSPECTION (TC# 20061101005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1G72 3U      H1NE                         
20061205002062006120500206EA  2006       12         5          CA061102001      120061029G5610NP1393215       WINDSHIELD                              CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              COCKPIT         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) LT WINDSHIELD REMOVED AND REPLACED ACC AMM TASK 56-11-01-000-801. (TC# 20061102001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F4  FRTA21EA   E15NE                
20061205002362006120500236EA  2006       12         5          CA061102002      120061026G5610601R3303314     WINDSHIELD                              CNDAIRCL600 CL6002C10   1390015EA  GE    CF34  CF348C1          NE                              COCKPIT         CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         APAPPROACH       1                      CA                                                                      (CAN) WINDSHIELD CHANGED AND TESTED IAW AMM TASK 56-11-01-401-801-A01.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA21EA   EOOO63EN             
20061205002382006120500238EA  2006       12         5          CA061102003      120061026G5610NP13932113      WINDSHIELD                              CNDAIRCL600 CL6002C10   1390015EA  GE    CF34  CF348C1          NE                              COCKPIT         FAILED          W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) CAPTAIN WINDSHIELD SHATTERED AT FL320 ENROUTE TO ORD.  DIVERTED TO BIS. (TC# 20061102003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA21EA   EOOO63EN             
20070126003062007012600306CE  2007       1          26         CA061102004      120061102G27202613017202      RUDDER                                  CESSNA208   208B        2073701CE                                                                               STIFF           W      D   RETURN TO BLOCK                                                                                 F  FLT CONT AFFECTED                                                             TXTAXI/GRND HDL  1                      CA       4088 4088                                                      (CAN) AIRCRAFT WAS BEING TAXIED TO THE RAMP FROM THE HANGER. THE PILOT NOTICED THAT THE RUDDER CONTROLS FELT STIFF.  THE PILOT DECIDED TO RETURN TO THE HANGER AND ADVISE MAINTENANCE. THE AIRCRAFT IS BEING EXAMINED AT THIS TIME AND WILL UP-DATE THIS SDR WHEN A CAUSE OF THIS FAULT IS FOUND. (TC NR 20061102004)                                                                                                                                                                                                                                                                                                                                                                                                                           1H71 3T      A37CE                        
20061205001742006120500174    2006       12         5          CA061102005      120061102G5412K6600013        FIREWALL                                                                   GARRTTTPE331TPE3315251K      NM                              NACELLE         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) CRACKS FOUND IN FIREWALL ASSEMBLY WHILE DOING SB 217. (TC# 20061102005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          4  T          E2WE                 
20061211003452006121100345NM  2006       12         11         CA061102006      120061004G3230                HOUSING         TACTAIR                 DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF23      NE  SEQUENCE VALVE  FAILED          W      A   UNSCHED LANDING                                                                                 K  FLUID LOSS                                                                    APAPPROACH       1                      CA       13093      1769                                                (CAN) DURING APPROACH WHEN CREW SELECTED GEAR DOWN, NR 2 HYD ENG PUMP CAUTION LIGHT ILLUMINATED DURING EXTENSION CYCLE. NOSE GEAR DOORS AND RT MAIN GEAR DOORS REMAINED OPEN, LT MAIN GEAR DOOR CLOSED. QRH ITEMS FOR NR 2 HYDRAULIC SYSTEM AND GEAR DOORS OPEN WERE COMPLETED. INVESTIGATION BY ENGINEERING DETERMINED THAT THE LEAK WAS ORIGINATING FROM THE RT MLG DOOR SOLENOID SEQUENCE VALVE.  (3) OF THE FOUR BOLTS SECURING THE SOLENOID TO THE VALVE BODY HAD SHEARED RESULTING IN THE PARTIAL SEPARATION OF THE SOLENOID FROM VALVE BODY. THIS CAUSED A LOSS OF NR 2 HYDRAULIC SYSTEM QUANTITY AND PRESSURE. NO SECONDARY DAMAGE WAS CAUSED AS A RESULT OF THE FAILURE. THE SOLENOID SEQUENCE VALVE ASSEMBLY WAS REPLACED IAW THE AIRC2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20061211003472006121100347EA  2006       12         11         CA061102007      120060926G5751                HINGE           BOMBDR                  CNDAIRCL215 CL2156B11215       EA  PWA   PW120 PW123            NE  HAMSTD14SF  14SF*       NE  AILERON         DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2936                                                           (CAN) DURING AN ANNUEL INSPECTION WE FOUND BOTH AILERONS WITH SEVERE DAMAGE AT CENTER HINGE (TC NR 20061102007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2H72 4T4  TRTA14EA   E20NE   6  CP7NE     
20061205001762006120500176NM  2006       12         5          CA061103002      120061101G574072760059101     ADAPTER                                 DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  ACTUATOR        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       48562      1341                                                (CAN) A CRACK WAS DISCOVERED (C-CHECK INSPECTION) ON THE RUDDER ACTUATOR MOUNTING ADAPTOR (UPPER) TO VERTICAL STAB SPAR. THE CRACK IS APPROXIMATELY 2.5 INCHES AROUND THE CIRCUMFERENCE OF THE ADAPTOR TUBE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20061211003492006121100349NE  2006       12         11         CA061103003      220060927G7200                ENGINE                                  CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE                                              OVERHEATED      W      O   OTHER                                                                                           MJ OVER TEMP                 WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA                                          PC1299                      (CAN) DURING TAXI FOLLOWING LANDING THE ENGINE EXPERIENCED AN ITT OVER-TEMPERATURE.  SUBSEQUENT INSPECTION REVEALED DEBRIS IN THE EXHAUST AND HEAT DISCOLORATION OF THE AIRCRAFT COWLING IN THE EXHAUST REGION.  MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061103003)                                                                                                                                                                                                                                                                                                                                                                                                                               1H71 3T3  T  A37CE   E4EA                 
20061211003512006121100351EA  2006       12         11         CA061103004      220060925G7261                OIL SYSTEM                              SOCATATBM   TBM700      8682000EU  PWA   PT6   PT6A64           EA                              ENGINE          OVERTEMP        W      E   ENGINE SHUTDOWN                                                                                 MJ OVER TEMP                 WARNING INDICATION                                  NRNOT REPORTED   1                      CA                                                                      (CAN) IN FLIGHT ENGINE OIL TEMPERATURE WAS SEEN TO INCREASE ACCOMPANIED BY A DROP IN OIL PRESSURE.  THE ENGINE WAS SHUTDOWN IN FLIGHT.  POST FLIGHT INSPECTION REVEALED DEBRIS IN THE ENGINE OIL SYSTEM AND EVIDENSE OF OIL LEAKAGE FROM THE ENGINE DRAIN.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061103004)                                                                                                                                                                                                                                                                                                                                                                                       1L71 3T4  TRTA60EU   E4EA                 
20061211003522006121100352NE  2006       12         11         CA061103005      220060927G7210                SHAFT                                   BOMBDRDHC8  DHC8400            NM  PWA   PW120 PW123            NE                              RGB             DAMAGED         W      O   OTHER                                                                                           XJ ENGINE FLAMEOUT           WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) THE ENGINE FLAMED-OUT IN CRUISE AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED METAL DEBRIS ON THE ENGINE CHIP DETECTOR AND DAMAGE TO THE TOWERSHAFT.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061103005)                                                                                                                                                                                                                                                                                                                                                                                                                                                    2H72 4T4  TRTA13NM   E20NE                
20061211003532006121100353NE  2006       12         11         CA061103006      220060810G7261                TUBE                                    AEROSPATR42 ATR42*      8680900EU  PWA   PW121 PW121       52124NE                              OIL TRANFER     CRACKED         W      E   ENGINE SHUTDOWN                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  TOTAKEOFF        1                      CA                                          121355                      (CAN) FOLLOWING TAKEOFF ENGINE SPEEDS REDUCED UNCOMMANDED AND AN ENGINE FIRE WARNING ACTIVATED.  THE ENGINE WAS SHUTDOWN IN FLIGHT. SUBSEQUENT INSPECTION FOUND THE PROPELLER DIFFICULT TO ROTATE, EVIDENCE OF OVER-HEATING ON THE GAS GENERATOR CASE, AND A FRACTURED OIL TRANSFER TUBE.  MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061103006)                                                                                                                                                                                                                                                                                                                                                     2H72 4T4  TRTA53EU   E20NE                
20061211003542006121100354NE  2006       12         11         CA061103007      220060923G7250                TURBINE BLADES                          CESSNA425   425         2076018CE  PWA   PT6   PT6A112     52043NE                              ENGINE          FRACTURED       W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                          12439                       (CAN) IN FLIGHT THE ENGINE EMITTED A LOUD NOISE FOLLOWED BY FLAMES FROM THE EXHAUST AND VIBRATION.  THE ENGINE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED FRACTURED COMPRESSOR TURBINE BLADES.  MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061103007)                                                                                                                                                                                                                                                                                                                                                                                                                                   1L72 3T3  TRTA7CE    E4EA                 
20061211003562006121100356NE  2006       12         11         CA061103008      220060902G7321324485718       FUEL CONTROL                            DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE                              ENGINE          FAULTY          W      O   OTHER                                                                                           XJ ENGINE FLAMEOUT           WARNING INDICATION                                  CLCLIMB          1                      CA       3144                                                           (CAN) THE ENGINE FLAMEOUT IN CLIMB AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  THE HYDROMECHANICAL FUEL CONTROL UNIT WAS SUBSEQUENTLY REPLACED.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061103008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2H72 4T4  TRTA13NM   E20NE                
20061211003572006121100357NE  2006       12         11         CA061103009      220061005G7200                ENGINE                                  AEROSPATR42 ATR42*      8680900EU  PWA   120   PW120            NE                                              FAILED          W      E   ENGINE SHUTDOWN                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  TOTAKEOFF        1                      CA                                          120100                      (CAN) ON TAKEOFF ENGINE POWER REDUCED UNCOMMANDED FOLLOWED BY SMOKE IN THE CABIN AIR.  THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION FOUND THE PROPELLER SEIZED AND METAL DEBRIS IN THE ENGINE CASES.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061103009)                                                                                                                                                                                                                                                                                                                                                                                2H72 4T4  TRTA53EU   E20NE                
20061211003582006121100358NE  2006       12         11         CA061103010      220061007G7321                FUEL CONTROL                            CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE                              ENGINE          FAULTY          W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         F  FLT CONT AFFECTED                                                             CLCLIMB          1                      CA                                                                      (CAN) ON TAKEOFF ENGINE POWER INCREASED UNCOMMANDED AND THE ENGINE WOULD NOT RESPOND TO THROTTLE INPUT.  THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20061103010)                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3T3  T  A37CE   E4EA                 
20061205001722006120500172EA  2006       12         5          CA061103011      120061102G2750                CONTROL UNIT                            CNDAIRCL600 CL600*             EA  GE    CF34  CF343A      30015NE                              TE FLAPS        FAILED          W      A   UNSCHED LANDING                                                                                 F  FLT CONT AFFECTED                                                             CLCLIMB          1                      CA                                                                      (CAN) DURING  TAKE OFF FLAP FAIL DURING FLAP RETRACTION, A/C RETURN TO TERMINAL .BREAKER RESET AS PER OPERATING MANUAL NR 1 ABNORMAL PROCEDURE SECTION 10 P 3-4. A/C RETURN TO SERVICE ,NO FURTHER SNAG.TWO MORE TAKE -OFF WERE CARRIED OUT FOLLOWING THAT INCIDENT, NO SNAG.                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  FRTA21EA   E15NE                
20061211003602006121100360NE  2006       12         11         CA061103012      220061012G73201240KDC0400     EEC                                     LEAR  60    60LEAR      5170707CE  PWA   305   PW305A      52128NE                                              FAILED          W      O   OTHER                                                                                           XJ ENGINE FLAMEOUT           WARNING INDICATION                                  DEDESCENT        1                      CA                                                                      (CAN) THE ENGINE FLAMED OUT ON DESCENT.  THE PROBLEM COULD NOT BE DUPLICATED ON THE GROUND AND THE EEC WAS SUBSEQUENTLY REPLACED.  MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061103012)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F4  FRTA10CE   E35NE                
20061211003622006121100362NE  2006       12         11         CA061103013      220061005G7250                TURBINE BLADES                          BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE                              ENGINE          DAMAGED         W      C   ABORTED TAKEOFF                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  TOTAKEOFF        1                      CA                                          PS0469                      (CAN) ON TAKEOFF ROLL THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY A LOSS IN POWER.  TAKEOFF WAS ABORTED.  SUBSEQUENT INSPECTION REVEALED DAMAGED POWER TURBINE BLADES.  MFG WILL MONITOR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061103013)                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4T4  TRTA24CE   E26NE                
20070126003072007012600307SW  2007       1          26         CA061103014      120061030G29102781006025      HYDRAULIC LINE                          SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE33111U   01514WP  MCAULY4HFR344HFR34C652  NE  LT MLG WW       CRACKED         W      O   OTHER                                                                                           K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) HYD FLUID LEAKING FROM LT WHEEL WELL.  WHEN LT GEAR DOORS WERE OPENED TO INSPECT, ENTIRE GEAR BAY WAS COVERED WITH FLUID.  AFTER CLEANING, REPLACING LINE AND PUTTING AIRCRAFT ON JACKS TO CHECK FOR FURTHER LEAKS ALL CHECKED WITHIN MANUFACTURERS LIMITATIONS.  AIRCRAFT RETURNED OT SERVICE. (TC NR 20061103014)                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4T4  TRTA8SW    E4WE    6  C3PNE     
20061205002992006120500299NE  2006       12         5          CA061103015      220061014G7250                TURBINE BLADES                          CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              ENGINE          FRACTURED       W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         E  VIBRATION/BUFFET                                                              CRCRUISE         1                      CA                                                                      (CAN) IN CRUISE THE ENGINE EXPERIENCED VIBRATIONS FOLLOWED BY A LOUD NOISE AND WAS SHUT DOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED FRACTURED TURBINE BLADES.  P&WC WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC# 20061103015)                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L72 4F4  F  A22CE   E1NE                 
20061205002142006120500214NE  2006       12         5          CA061103016      220061027G7200                ENGINE                                  CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                                              FLAMED OUT      W      O   OTHER                                                                                           XJ ENGINE FLAMEOUT           WARNING INDICATION                                  NRNOT REPORTED   1                      CA                                          71397                       (CAN) THE ENGINE FLAMED OUT IN FLIGHT FOLLOWING A COMMANDED REDUCTION IN POWER TO IDLE.  PWC WILL MONITOR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC# 20061103016)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L72 4F4  F  A22CE   E1NE                 
20061205001962006120500196GL  2006       12         5          CA061103017      220061030G724023064570B       COMBUSTION LINER                        BELL  407   407         1182206SW  ALLSN 250C  250C47B          GL                              ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                          CAE847206                   (CAN) COMBUSTION LINER FOUND CRACKED ON REMOVAL DURING TURBINE SECTION REPLACEMENT TO COMPLY WITH ROLLS ROYCE CEB A-72-6060. THIS PART IS FOUND TO BE CRACKED ANY TIME IT IS REMOVED AFTER ANY LENGTH OF TIME IN SERVICE. MANUFACTURERS MAINTENANCE MANUAL ALLOWS NO CRACKS IN THIS AREA.                                                                                                                                                                                                                                                                                                                                                                                                                                                       1G71 3U3  UO H2SW    E1GL                 
20061205001982006120500198GL  2006       12         5          CA061103018      220061030G724023030911K       COMBUSTION CASE                         BELL  407   407         1182206SW  ALLSN 250C  250C47B          GL                              ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                          CAE847206                   (CAN) CRACK ALONG LEFT SIDE "ARMPIT" WELD LINE FOUND DURING UNSCHEDULED TURBINE REMOVAL FOR CEB A-72-6060. NO CRACKS ALLOWED IN THIS AREA.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3U3  UO H2SW    E1GL                 
20061205001772006120500177EU  2006       12         5          CA061104001      120061101G5510258TF4331       PLATE                                   BRAERODH125 BAE125800A  1500285EU                                                               HORIZONTAL STAB CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       6160                                                           (CAN) UPON VISUAL INSPECTION AND CLEANING OF ATTACHMENT LUG AREA OF VERTICAL FIN TO HORIZONTAL STABILIZER, MECHANIC NOTICED MATERIAL FLAKING OFF OF ONE BOLT HOLE. FURTHER INSPECTION REVEALED EXFOLIATION CORROSION. SINCE THIS TYPE OF CORROSION IS DIFFICULT TO DETECT VISUALLY IT WAS ONLY WHEN THE MECHANIC WAS CLEANING THE AREA THAT HE NOTICED THE DAMAGE. UPON CONSULTATION WITH THE MANUFACTURER (RAYTHEON) THE CORROSION WAS REMOVED TO DETERMINE THE EXTENT OF PENETRATION AND COVERAGE (PHOTO ILLUSTRATION) WHICH WAS DETERMINED TO BE OUT-OF-TOLERANCE AND REQUIRED REPLACEMENT OF THE REINFORCEMENT PLATE. THIS DEFECT WAS THE FIRST TIME THE MANUFACTURER HAD COME ACROSS. ESPECIALLY SIGNIFICANT WAS THE FACT THAT IT WAS EXFOL2L72 4F    RTA3EU                         
20061211003632006121100363NE  2006       12         11         CA061106001      220060821G7210311196801       SHAFT                                   EMB   120   EMB120      3260201SO  PWA   PW118 PW118B           NE                                              FRACTURED       W      O   OTHER                                                                                           XJ ENGINE FLAMEOUT           WARNING INDICATION                                  NRNOT REPORTED   1                      CA       26695                                                          (CAN) THE ENGINE SUFFERED AN IN FLIGHT SHUTDOWN AS A RESULT OF A FRACTURED TOWER SHAFT. (TC NR 20061106001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4T4  TRTA31SO   E20NE                
20061205002582006120500258NE  2006       12         5          CA061106002      220061019G7261                ENGINE                                  DHAV  DHC8  DHC8201     2809001NM  PWA   120   PW123D      52152NE                                              LEAKING         W      O   OTHER                                                                                           KB FLUID LOSS                SMOKE/FUMES/ODORS/SPARKS                            NRNOT REPORTED   1                      CA                                          123308                      (CAN) THE AIRCRAFT LAVATORY SMOKE DETECTOR ACTIVATED SHORTLY AFTER TAKE OFF AND OIL SMELL BECAME EVIDENT IN THE CABIN.  A SMALL EXTERNAL ENGINE OIL LEAK WAS SUBSEQUENTLY FOUND.  &WC WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC# 20061106002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                2H72 4T4  TRTA13NM   E20NE                
20061205002972006120500297NE  2006       12         5          CA061106003      220061015G7200                ENGINE                                  AEROSPATR42 ATR42300    8680920EU  PWA   120   PW120            NE                                              SHUTDOWN        W      O   OTHER                                                                                           RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  NRNOT REPORTED   1                      CA                                                                      (CAN) THE ENGINE WAS REPORTED TO HAVE EXPERIENCED THREE INCIDNETS OF TORQUE FLUCTUATION RESULTING IN EITHER PROPELLER FEATHERING OR IN-FLIGHT SHUT-DOWN BETWEEN OCTOBER 15TH AND 17TH.  THE ENGINE FUEL SYSTEM COMPONENTS WERE SUBSEQUENTLY REMOVED FOR INVESTIGATION.  P&WC WILL MONITOR THE INVESTIGATION AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC# 20061106003)                                                                                                                                                                                                                                                                                                                                                                         2H72 4T4  TRTA53EU   E20NE                
20061205002422006120500242NE  2006       12         5          CA061106004      220061025G73218236602         HYDROMECH UNIT                          CESSNA500   560CESSNA   2076750CE  PWA   530   PW535A           NE                              ENGINE          MALFUNCTIONED   W      O   OTHER                                                                                           XJ ENGINE FLAMEOUT           WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) THE ENGINE FLAMED-OUT IN CRUISE AND THE AIRCRAFT DIVERTED FOR A SINGLE ENGINE LANDING.  THE HYDROMECHANIAL FUEL CONTROL UNIT WAS SUBSEQUENTLY REPLACED.  P&WC WILL MONITOR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC# 20061106004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRTA22CE   E00053EN             
20061205002982006120500298EA  2006       12         5          CA061106005      220061015G7200                ENGINE                                  BELL  212   212         1181420SW  PWA   PT6T  PT6T3       52045EA                                              MALFUNCTIONED   W      E   ENGINE SHUTDOWN                                                                                 BJ SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION                                  NRNOT REPORTED   1                      CA                                          60244                       (CAN) DURING GROUND RUNS FOLLOWING EXTENSIVE MAINTENANCE THE POWER SECTION ACCELERATED UNCOMMANDED.  POWER WAS REDUCED TO IDE AND THE ENGINE LOW OIL PRESSURE WARNING ACTIVATED.  ON SHUT DOWN SMOKE WAS SEEN EMINATING FROM THE EXHAUST.  SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES AND RESULTANT ENGINE DAMAGE.  PWC WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC# 20061106005)                                                                                                                                                                                                                                                                                                              1G71 4U4  U  H4SW    E22EA                
20061205001802006120500180NE  2006       12         5          CA061106006      220061101G7200                ENGINE                                  AEROSPATR42 ATR42300    8680920EU  PWA   120   PW120            NE                                              FAILED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                          120983                      (CAN) IN CRUISE THE ENGINE EMITTED A LOUD NOISE AND ENGINE ITT TEMPERATURE WAS SEEN TO INCREASE.  POST-FLIGHT INSPECTION FOUND THE PROPELLER COULD NOT BE ROTATED.  P&WC WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2H72 4T4  TRTA53EU   E20NE                
20061205002432006120500243NE  2006       12         5          CA061106007      220061024G73203035381         TUBE                                    DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  FUEL SYSTEM     FRACTURED       W      E   ENGINE SHUTDOWN                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) ENGINE POWER REDUCED TO IDLE UNCOMMANDED IN CRUISE.  AN EMERGENCY WAS DECLARED AND THE ENGINE WAS SHUT DOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED A FRACTURED FUEL CONTROL P3 AIR SUPPLY TUBE.  THE FRACTURE HAD OCCURRED IN THE WELD AREA AT THE TUBE "B" NUT. (TC# 20061106007)                                                                                                                                                                                                                                                                                                                                                                                                                                                    2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20061205000962006120500096EA  2006       12         5          CA061106008      120061103G2497M2750010JB3U00  WIRE HARNESS                            CNDAIRCL600 CL600*             EA                                                               ADG             SHORTED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       7305                                                           (CAN) ADG DROPPED IN FLIGHT FOR TEST, NO POWER, LANDED NORMALLY. FOUND WIRING HARNESS AND WIRES BURNED & SHORTED AT CONNECTOR P1XC ON ADG. BOMBARDIER PSP603A WIRING MANUAL 24-25-01 FIG. 1 SHEET1. WIRING HARNESS AND CONNECTOR REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F    RTA21EA                        
20061205000972006120500097EU  2006       12         5          CA061106009      120061103G2910137311D1431     LINE                                    BAG   JETSTMJETSTM3212  1500217EU                                                               HYD SYSTEM      CHAFED          W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) L/H HYDRAULIC BRAKE LINE FOUND LEAKING FLUID. LEAK FOUND AT MYCARTA CLAMPING BLOCK. NEW LINE INSTALLED. (TC# 20061106009)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4T    RTBA15CAA                      
20070126003092007012600309EU  2007       1          26         CA061106011      120061102G3010FAL1007         HOSE                                    AMD   FALC10FALCON10    2730101EU  GARRTTTFE731TFE7312     01518WP                              LT SLAT         COLLAPSED       W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA       306                                                            (CAN) AFTER LANDING THE PILOTS NOTICED THAT THE LT IB SLAT HAD A SMALL TRACE OF ICE FORMED.  AFTER INSPECTION IT WAS FOUND THAT THE LT IB SLAT ANTI-ICE HOSE INNER WALL HAD COLLAPSED.  THE HOSE WAS REPLACED AND ALL OTHER SLAT ANTI-ICE HOSES WERE INSPECTED AND FOUND SERVICEABLE. (TC NR 20061106011)                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F4  F  A33EU   E6WE                 
20061205003142006120500314GL  2006       12         5          CA061106012      320061013G6111163356          SEAL                                                                                                        MCAULYD3A36 D3A36C410   GL  BLADE ROOTS     INCORRECT       W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA       63                                                             (CAN) PROPELLER WAS FACTORY ASSEMBLE WITH INCORRECT BLADE SEALS ON ALL 3 BLADES. P/N 1633-56 SHOULD HAVE BEEN INSTALL BUT SEALS FOR A NON-OIL FILLED HUB WERE FOUND INSTALLED INSTEAD. THIS WAS A WARRANTY REPAIR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           5  CP47GL    
20061205002122006120500212SW  2006       12         5          CA061106014      120061027G3230                LANDING GEAR                            BELL  430   430         1182150SW                                                                               MALFUNCTIONED   W      O   OTHER                                                                                           O  OTHER                                                                         LDLANDING        1                      CA                                                                      (CAN) ON APPROACH TO HELIPAD, LANDING GEAR DID NOT BE DEPLOYED. PILOT NOTICE AT THE LAST MOMENT AND ALMOST LANDED ON BELLY. ADD NO GREEN LIGHT NOR AUDIO WARNING. USE THE EMERGENCY GEAR RELEASE. LANDING UNEVENTFUL AFTERWARD. (TC# 20061106014)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1G72 3U    RTH9SW                         
20061205002522006120500252EA  2006       12         5          CA061106015      220061022G72303023779         DIFFUSER                                DHAV  DHC7  DHC7102     2802708EA  PWA   PT6   PT6A50      52043EA  HAMSTD24PF  24PF305     GL  ENGINE          LOOSE           W      A   UNSCHED LANDING                                                                                 XJ ENGINE FLAMEOUT           WARNING INDICATION                                  CRCRUISE         1                      CA                                          86199                       (CAN) SHORTLY AFTER LEVELLING OFF AT 17000 FEET, THE NR 2 ENGINE BEGAN TO SURGE AFFECTING ALL ENGINE PARAMETERS.  THE POWER WAS REDUCED TO ALLEVIATE THE RESULTING OVER TEMPERATURE CONDITION. AT POWER SETTING ABOVE 70% NG THE ITT WOULD FLUCTUATE WILDLY TO OVER 900 DEGREES. THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT. AFTER TROUBLESHOOTING, THE ENGINE WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. THE ENGINE WAS SPLIT AND THE DIFFUSER TUBE AT 6 O-CLOCK WAS FOUND LOOSE. THIS LOOSE DIFFUSER TUBE DISRUPTED THE AIRFLOW TO THE BLEED VALVE SENSE LINE, CAUSING THE BLEED VALVES TO MALFUNCTION AND THE ENGINE TO SURGE. THE ENGINE WAS SENT FOR REPAIR.                                         2H74 4T4  T  A20EA   E4EA    6  CP1NE     
20061205000852006120500085CE  2006       12         5          CA061106016      120061104G27501015210579      SWITCH                                  BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE  HARTZLHCE4A HCE4A3I     NE  TE FLAPS        FAILED          W      A   UNSCHED LANDING                                                                                 F  FLT CONT AFFECTED                                                             DEDESCENT        1                      CA       15902                                                          (CAN) AFTER TWO MISSED APPROACHES, THE FLAPS WOULD NOT RETRACT FROM 17 DEGREES. AIRCRAFT DIVERTED, ON THE GROUND THE FLAP ASYMETRICAL OVERRIDE SWITCH WAS USED AND FLAPS RETRACTED. THE FLAPS WHERE THEN DEFERRED UNTIL MAINTENANCE INPECTED SYSTEM AND FOUND FAULTY ASYMETRICAL SWITCH. SWITCH WAS REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4T4  TRTA24CE   E26NE   5  CP10NE    
20061205000862006120500086CE  2006       12         5          CA061106017      120061104G79311013890235      TRANSDUCER                              BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE                              OIL PRESSURE    MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      CA       9301                                                           (CAN) ON CLIMB NR 2 ENGINE DISPLAYED OIL PRESSURE FLUCTUATIONS FROM 120 TO 60 PSI. NO LOW OIL PRESSURE LIGHTS ILLUMINATED AND NO TORQUE FLUCUATIONS. THEY ELECTED TO RETURN TO AIRPORT. MAINTENANCE REPLACED THE R/H OIL PRESSURE TRANSDUCER AND AIRCRAFT WAS TESTED AND RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4T4  TRTA24CE   E26NE                
20061205000872006120500087EA  2006       12         5          CA061106018      220061103G72303035279         LINE                                    DHAV  DHC7  DHC7103     2802710EA  PWA   PT6   PT6A50      52043EA  HAMSTD24PF  24PF305     GL  P3 SENSE        BROKEN          W      E   ENGINE SHUTDOWN                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA                                          PCE86509                    (CAN) WHILE IN CRUISE THE NR 3 ENGINE ROLLED BACK TO 60% NG.. A PRECAUTIONARY SHUT DOWN OF THE ENGINE WAS COMPLETED AND THE AIRCRAFT RETURNED TO BASE. ON INSPECTION OF THE ENGINE IT WAS FOUND THAT THE P3 SENSE LINE, FROM THE GAS GENERATOR CASE TO THE P3 FILTER, WAS BROKEN, CAUSING THE ENGINE TO ROLL BACK TO IDLE. THE SENSE LINE WAS  POST P&WC S/B-4112. THIS S/B INTRODUCED A BRACKET TO HELP SUPPORT THE LINE AT THE GAS GENERATOR ATTACHMENT END. THE LINE WAS REPLACED WITH A SERVICEABLE PART, AN ENGINE RUN-UP WAS COMPLETED AND FOUND TO BE SERVICEABLE.                                                                                                                                                                       2H74 4T4  T  A20EA   E4EA    6  CP1NE     
20061205001732006120500173EA  2006       12         5          CA061107001      120061102G2722AL00102         ACTUATOR                                CNDAIRCL600 CL6002C10   1390015EA                                                               RUDDER TRIM     MALFUNCTIONED   W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA       6372                                                           (CAN) DISC-RUDDER TRIM MOVING ON ITS OWN WITHOUT INPUT FROM COCKPIT CONTROLS. PULLED C/B 2F2 IAW AOM VOL 1. INDICATOR STILL SHOWS UNCOMMANDED MOVEMENT AND PLANE STILL FLIES SIDEWAYS, FDR DOWLNLOAD WAS REQUESTED TO CONFIRM THE TRIM MOUVEMENT. MAINTENANCE WAS UNABLE TO DUPLICATE.  THE RUDDER TRIM ACTUATOR WAS REPLACED IAW CRJ700 AMM 27-22-01 AND PERFORMED FUNCTIONAL TEST OF THE RUDDER TRIM SYSTEM. FOUND SYSTEM WORKING PROPERLY AT THIS TIME IAW CRJ700 AMM 27-22-00.                                                                                                                                                                                                                                                              2L72 4F    RTA21EA                        
20061205001572006120500157EA  2006       12         5          CA061107002      120061103G7120ASB1810617      BOLT                                    CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              ENGINE MOUNT    UNSECURE        W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA                                                                      (CAN) AFT ENGINE MOUNT THRUST FITTING ATTACHMENT BOLTS ARE NOT SECURED (TORQUE IS UNKNOWN AND LOCKWIRE IS NOT INSTALLED) AT RH ENGINE. TO COMPLETE THE PROCEDURE IAW AMM 71-22-01 ENGINE TO BE REMOVED. (TC# 20061107002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F4  FRTA21EA   E15NE                
20061205001702006120500170NM  2006       12         5          CA061107003      120061102G29136617303         PUMP                                    BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                              HYD SYSTEM      FAILED          W      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  DEDESCENT        1                      CA            1262                                                      (CAN) DURING DECENT TO THE AIRPORT PILOTS OBSERVED LOSS OF NR 2 HYD PRESSURE AND NR 2 EDP CAUTION LIGHT. THE PTU WAS SELECTED ON AND THE NR 2 HYD PRESSURE RECOVERED AND FLUID QUANTITY HAD DROPPED TO 40%. CREW ELECTED TO RETURN TO BASE. NON-EMERGENCY LANDING AND AIRCRAFT TAXIED TO RAMP UNDER ITS OWN CONTROL.  NR 2 EDP HAD INTERNAL ROTATING GROUP FAILURE, EDP REPLACED.                                                                                                                                                                                                                                                                                                                                                               2H72 4T4  TRTA13NM   E00062EN             
20061205001712006120500171SW  2006       12         5          CA061107004      120061102G5210AR835OXT4619    HANDLE                                  BELL  412   412EP       1182205SW                                                               PAX DOOR        MISSING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2                                                              (CAN) UPON TEST FLIGHT RETURN TO BASE, IT WAS NOTICED THAT THE CO-PILOT OUTSIDE DOOR HANDLE WAS MISSING, SUSPECT IT WAS LOST IN FLIGHT. (TC# 20061107004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1G72 4U      H4SW                         
20061205000832006120500083NM  2006       12         5          CA061107005      120061105G5610NP15790112      WINDSHIELD                              DHAV  DHC8  DHC8301     1386003NM                                                               COCKPIT         CRACKED         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA       20816                                                          (CAN) DURING CLIMB OUT, ALTITUDE APPROX. FL70, THE CO-PILOT NOTICED A SMALL CRACK IN THE MIDDLE OF HIS WINDSHIELD, WHICH WAS GETTING RAPIDLY BIGGER. EMERGENCY CHECKLIST FOR CRACKED WINDSHIELD WAS PERFORMED. RELANDING WAS UNEVENTFUL. A/C HANDED OVER TO MAINTENANCE. CO-PILOT`S WINDSHIELD REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                        2H72 4T    RTA13NM                        
20070126003142007012600314NM  2007       1          26         CA061107008      120061101G33103280080         TRIM PANEL                              DORNERDO32  DO328100    2996000NM  PWA   119   PW119C           NE  HARTZLHDE6C HDE6C3B     NE  COCKPIT         SHORTED         W      K   NONE                                                                                            B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA       6671                                                           (CAN) ENROUTE THE PILOT REPORTED A STRONG SMELL AND A FLASH OF LIGHT FROM CENTER CONSOLE AREA. THEY TURNED THE INTERIOR DOME LIGHT ON A CONFIRMED THAT A PLASTIC LIGHTING PANEL WAS MELTING ON THE RUDDER LIMITER AND STANDBY ELEVATOR BUTTONS. HE POKED THE SPOT WITH A PEN WHICH RESULTED IN FURTHER ARCING AND SMOKE. HE REQUESTED A LOWER ALTITUDE AND LANDED. MAINTENANCE WAS CONTACTED AND DISPATCHED TO THE AIRCRAFT. MAINTENANCE FOUND THE LIGHTING PANEL FOR THE TRIM HAD SHORTED. IT WAS DISABLED AND THE INTERIOR LIGHTING TESTED WITH NO FURTHER PROBLEMS. THE ITEM WAS DEFERRED AND THE AIRCRAFT RETURNED TO SERVICE.  THE PILOT REPORTED THAT THE CB DID NOT POP AND THAT HE HAD A HARD TIME IN LOCATING THE CORRECT CB TO ISOLATE2H72 4T4  TRTA45NM   E20NE   6  CP34NE    
20061205000772006120500077EA  2006       12         5          CA061107009      220061106G7414                DISTRIBUTOR GEARCONT                    ROBSINR44   R44         7640120WP  LYC   O540  O540F1B5    41532EA                              MAGNETO         FAILED          W      O   OTHER                                                                                           R  PARTIAL RPM/PWR LOSS                                                          CRCRUISE         1                      CA       249        E01HA137R                                           (CAN) DURING CRUISE FLIGHT, THE PILOT NOTICED A CHANGE IN ENGINE NOISE AND A SLIGHT YAW FOLLOWED BY THE LOW ROTOR HORN. PILOT DECREASED POWER WHICH RESULTED IN THE ROTOR RPM RECOVERING TO A NORMAL SETTING. THE PILOT FINISHED THE SHORT FLIGHT AT A LOWER POWER SETTING AND LANDED THE AIRCRAFT WITHOUT FURTHER INCIDENT. AFTER LANDING, A MAGNETO CHECK WAS CONDUCTED WHICH RESULTED IN THE ENGINE QUITING WHEN THE R/H MAG WAS SELECTED. WHEN THE MAGNETO WAS REMOVED, A FEW TEETH WERE FOUND BROKEN OFF THE DISTRIBUTOR GEAR.                                                                                                                                                                                                             1G71 3O3  O  H11NM   E295                 
20061205001602006120500160EA  2006       12         5          CA061107011      120061103G213092E204          CHECK VALVE                             CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30015NE                              PRESS BULKHEAD  FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         DEDESCENT        1                      CA                                                                      (CAN) THE CREW REPORTED THAT ON DESCENT THEY HAD PRESSURIZATION PROBLEMS. DURING THE DESCENT THEY GOT AUTO PRESS1 AND AUTO PRESS 2 FAIL AND MASKS DEPLOYED AND WERE USED. ALSO LT PACK HAD A BLOWN DUCT. LH PACK AIR CONDITIONING DUCT P/N601R895211-113 REPLACED BOTH 4.5 BUKHEAD CHECK VALVES REPLACED. NR 1 FOUND WITH NO SPRING LEFT. SB A601R-21-054 PG. 2 OF 18 EVIDENCE SECTION STATES: "AN AIRCRAFT WAS DEPRESSURIZED WHEN A FLAPPER ON THE BULKHEAD CHECK VALVE DETACHED AND AN AIR DUCT UPSTREAM OF THE BULKHEAD CHECK VALVE IS DISCONNECTED". BOTH CONSITIONS WERE PRESENT. O2 GENERATORS WERE REPLACED, SB APPLIED AND TEST FLIGHT WAS CARRIED OUT. AIRCRAFT RETURNED TO SERVICE.                                                   2L72 4F4  FRTA21EA   E15NE                
20061205000742006120500074EU  2006       12         5          CA061108001      120061107G5340350A35101700    MOUNT                                   SNIAS 350   AS350BA     8680817EU  TMECA ARRIELARRIEL1B    6OO30NE                              HYDRAULIC PUMP  DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING A 100 HOUR INSPECTION IT WAS DISCOVERED THAT TWO OF THE FOUR RIVETS USED TO ATTACH THE BEARING SUPPORT TO THE PUMP MOUNT WERE BROKEN.  THE BEARING SUPPORT AND ATTACHING RIVETS ARE NOT LISTED IN THE AS350 ILLUSTRATED PARTS CATALOG, AS THEY ARE PART OF THE PUMP MOUNT.  THE PUMP MOUNT WILL BE REPLACED AND THE AIRCARFT RETURNED TO SERVICE. (TC# 20061108001)                                                                                                                                                                                                                                                                                                                                                                1G71 3U3  UNCH9EU    E19EU                
20061211003672006121100367SW  2006       12         11         CA061108002      120060929G71202060621021      MOUNT                                   BELL  206   206B        1181511SW  ALLSN 250C  250C20      03013GL                              LT ENGINE       BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING DAILY INSPECTION PILOT NOTICED UNUSUAL PIECE OF METAL IN THE ENGINE BAY. INVESTIGATION REVEALED BROKEN LOWER LT ENGINE MOUNT. (TC NR 20061108002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1G71 3U3  U  H2SW    E4CE                 
20070126003152007012600315CE  2007       1          26         CA061108003      120060919G53205042002815      FLOOR SUPPORT                           BEECH 90    C90A        1152911CE  PWA   PT6   PT6A21      52043EA  HARTZLHCB3T HCB3TN3     GL  FUSELAGE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) FLOOR SUPPORT ANGLE P/N UNKNOWN FOUND CRACKED. ANGLE IS PART OF BULKHEAD ASSY. P/N 50420028-15. ANGLE IS LOCATED UNDER CENTRE FLOOR PANEL. (TC NR 20061108003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L72 3T4  TRT3A20    E4EA    6  CP15EA    
20070808001192007080800119CE  2007       8          8          CA061108004      120060828G552017121532        HINGE BRACKET                           CESSNA177   177B        2073708CE  LYC   O360  O360A1F6    41514EA  MCAULY2D34C B2D34C211   GL  RT STAB         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) RT STABILIZER HINGE BRACKET FOUND CRACKED AT FASTENER LOCATION. (TC NR 20061108004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3O3  O  A13CE   E286    5  CP7EA     
20061211003712006121100371EU  2006       12         11         CA061108005      120060912G5753137203B5761     BRACKET                                 BAG   JETSTMJETSTM3212  1500217EU  GARRTTTPE331TPE33110UG  01514WP  ROTOL R333  R333482F12  GL  TE FLAP         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) FLAP SLAT BRACKETS CRACKED AT RADIUS. (TC NR 20061108005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4T4  TRTBA15CAA E4WE    6  CP61GL    
20070126003182007012600318    2007       1          26         CA061108006      420061105G3497KG102A          CONNECTOR                               BEECH 76    76          1153005CE  LYC   O360  O360A1G6D        EA  HARTZLHCM2Y HCM2YR      GL  REMOTE GYRO     CONTAMINATED    W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) DURING TRAINING IN IMC CONDITIONS, ATC REPORTED TO STUDENT THAT HE WAS WAY OFF TRACK, PILOT CONFIRMED THAT HSI SYSTEM HAD FAILED. AIRCRAFT RETURNED TO BASE WITH HELP FROM ATC WITH NO OTHER INCIDENCE. MAINTENANCE DUPLICATED DEFECT, HSI SYSTEM INSPECTED AND FOUND WATER ON CONNECTOR TO REMOTE GYRO. CONNECTOR DRIED AND CLEANED, OPS CHECKED SYSTEM OK. GYRO IS LOCATED IN NOSE COMPARTMENT. CLOSE OUT PANEL CAN LET IN SMALL AMOUNTS OF WATER IF PANEL IS NOT FIT  PROPERLY BEFORE TIGHTENING THE SCREWS. THERE IS NO SEAL ON THIS PANEL. PANEL FIT AND INSTALLED CORRECTLY. (TC NR 20061108006)                                                                                                                                    1L72 3O3  O  A29CE   E286    5  CP43GL    
20061205001942006120500194EU  2006       12         5          CA061108008      120061030G3230                DIODE                                   BAG   JETSTMJETSTM3212  1500217EU                                                               MLG CONTROL     MELTED          W      O   OTHER                                                                                           FJ FLT CONT AFFECTED         WARNING INDICATION                                  APAPPROACH       1                      CA                                                                      (CAN) DEFECT LANDING GEAR FAILED TO EXTEND. CIRCUIT BREAKER RESET AS PER QRH. GEAR LOWERED NORMALLY.  RECTIFICATION LANDING GEAR WARNING SYSTEM TROUBLESHOT. FOUND DIODE 1GA28(P/N IN4007) TO BE MELTED. ALSO FOUND CAPACITOR 1GA26(P/N 114-19152) TO BE UNSERVICEABLE. NEW CAPACITOR AND DIODE INSTALLED. GROUND TEST CARRIED OUT AND FOUND SERVICEABLE. REF. W/O 1612 AND LOG PAGE 5037. DATE CLEARED OCTOBER 31, 2006. (TC# 20061108008)                                                                                                                                                                                                                                                                                                     2L72 4T    RTBA15CAA                      
20070808001202007080800120CE  2007       8          8          CA061109001      120061108G5520656530128       TUBE                                    CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              ELEVATOR        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING COMPLIENCE WITH CAMPAIGN NOTICE 851-27-20-035 (RUDDER AND ELEVATOR CABLE GUARDS) BOTH ELEVATOR CABLE GUARDS WERE FOUND TO BE UNSERVICEABLE. ALL (4) CLAMPS WERE DISTORTED AND CAUSED DISTORSION TO THE TUBES WHEN CLAMPED CAUSING CRACKS IN THE TUBES. BOTH ELEVATOR CABLE GUARD TUBES P/N 6565301-28 AND (4) CLAMPS P/N MS21919WD10 WERE REPLACE WITH NEW PARTS. THE RUDDER CABLE GUARDS WERE INSPECTED AND FOUND SERVICEABLE. (TC NR 20061109001)                                                                                                                                                                                                                                                                                1L72 4F4  F  A22CE   E1NE                 
20070808001212007080800121CE  2007       8          8          CA061109004      120060922G552012430192        BRACKET                                 CESSNA210   T210L       2073449CE  CONT  O520  TSIO520H    17040SO  MCAULY3A32C D3A32C88    GL  RT ELEVATOR     LOOSE           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) BRACKET P/N 1243019-2 FOUND LOOSE AGAINST TORQUE TUBE P/N 1234650-2. LOOSE FASTENERS REMOVED AND REPLACED. (TC NR 20061109004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H71 3O3  O  3A21    E8CE    5  CP21EA    
20061213000742006121300074EU  2006       12         13         CA061109005      120060904G5753137204B5167     BRACKET                                 BAG   JETSTMJETSTM3212  1500217EU  GARRTTTPE331TPE33110UG  01514WP  ROTOL R333  R333482F12  GL  TE FLAP         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                  SDJ13614                                            (CAN) IB FLAP P/N 13760B463, SLAT BRACKETS P/N 137204B51 AND 137205B67 FOUND CRACKED AT BEND RADIUS. REMOVED AND REPLACED WITH NEW. (TC NR 20061109005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4T4  TRTBA15CAA E4WE    6  CP61GL    
20080220000042008022000004SW  2008       2          20         CA061109006      120061109G5330                SKIN                                    BELL  206   206L4       1182110SW  ALLSN 25OC  250C20R          GL                              FUSELAGE        CRACKED         W      OK  OTHER                   NONE                                                                    O  OTHER                                                                         ININSP/MAINT     1                      CA       4113                                                           (CAN) CRACK FOUND IN SKIN UNDER FWD BEARING OIL COOLER SUPPORT RT STA 192.00 BUTT 4.0.  REPAIR WAS MADE IAW BHT-206-SRM-4-2 (TC NR 20061109006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1G71 3U3  UNCH2SW    E4CE                 
20061205001692006120500169NM  2006       12         5          CA061109007      120061102G3230104071          JOURNAL         MESSIER                 DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  MLG STAB        WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       4153021725 DCL2048797                                          (CAN) AIRCRAFT WAS POSITIONED ON GATE FOR NEXT FLIGHT. IT WAS THEN FOUND THAT RT MAIN LANDING GEAR PIN COULD NOT BE REMOVED. TROUBLESHOOTING BY MAINTENANCE FOUND ON THE FOLLOWING ON THE RT MAIN LANDING GEAR STABILIZER STAY ASSEMBLY. THE AFT LINED JOURNAL BUSHING (ITEM 305) FOUND TO HAVE EXCESSIVE WEAR (1/16TH 3/32ND) CAUSING THE DOWN LOCK PIVOT POINT LOCK LINK ASSEMBLY (ITEM 280) TO OVERCENTER TOO FAR. THE STAY ASSEMBLY WAS REPLACED PER DHC 8 AMM 32-10-26, OPERATION AND LEAK CHECKS CARRIED OUT WITH NO FAULTS, AND THE AIRCRAFT RETURNED TO SERVICE. REFERENCE MESSIER-DOWTY COMPONENT MAINTENANCE MANUAL 32-10-04 FIG 1, PAGES 1010-1016.                                                                                  2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20061205000732006120500073EA  2006       12         5          CA061109008      220061107G8520LW18729         PISTON                                  CESSNA150   152         2071835CE  LYC   O235  O235L2C     41505EA                              ENGINE          CRACKED         W      A   UNSCHED LANDING                                                                                 MBJOVER TEMP                 SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION        CRCRUISE         1                      CA       1005                                                           (CAN) HIGH OIL TEMPERATURE AND BURNING ODOR IN CABIN PROMPTED RETURN TO AIRPORT. COMPRESSION CHECK REVEALED LOW COMPRESSION NR 3 CYLINDER, REMOVAL REVEALED A PORTION OF THE SECOND RING LAND APPROX. 1.5 INCHES LONG BROKEN OFF THE PISTON AT THE 10 O`CLOCK POSITION VEIWED FROM TOP.                                                                                                                                                                                                                                                                                                                                                                                                                                                         1H71 3O3  ONT3A19    E223                 
20061212000822006121200082NM  2006       12         12         CA061110002      120060911G2530DL561064        MOTOR                                   BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  NR 3 OVEN       BURNED          W      A   UNSCHED LANDING                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA       9283       990412511                                           (CAN) A OPERATOR MADE A UNSCHEDULED LANDING DUE TO HEAVY SMELL COMING FROM AFT GALLEY. INVESTIGATION SHOWED THAT THE BLOWER MOTOR OF ONE GALLEY OVEN SHOWS BURN DAMAGE. OVEN REMOVED AND SENT FOR REPAIR. (TC NR 20061110002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
20080220000052008022000005SO  2008       2          20         CA061110003      120061109G30007961502         SHROUD          PIPER       7961502     PIPER PA28  PA28140     7102802SO  LYC   O320  O320E3D     41508EA  SNSNCH74D   74DM        EA  CABIN           OVERHEATED      W      K   NONE                                                                                            M  OVER TEMP                                                                     ININSP/MAINT     1                      CA       1356413564                                                     (CAN) PART FOUND DEFORMED ABD DISCOLORED AND HEAT BLISTERS. (TC NR 20061110003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L71 3O3  O  2A13    E274    5  NP88614   
20061205001672006120500167EU  2006       12         5          CA061110005      120061102G261237200000        FIRE DETECTOR                           AIRBUSA319  A319112     3930323EU  CFMINTCFM565CFM565B6    13802NE                              APU BAY         FAILED          W      O   OTHER                                                                                           N  FALSE WARNING                                                                 NRNOT REPORTED   1                      CA                                                                      (CAN) APU EMERG SHUTDOWN ECAM FOLLOWED BY FIRE WARN AND MASTER CAUTION, APU SHUTDOWN VIA MASTER SWITCH, ECAM APU EMERG SHUTDOWN MSG CONTINUED WITH FIRE WARN LIGHT. APU FIRE EXT BUTTON PUSHED, INDICATIONS REMAINED, FIRE BOTTLE DISCHARGED AS PRECAUTION. NO VISIBLE SIGNS OF FIRE OR SMOKE  NOTICED. FIRE WARN INDICATION REMAINED, AIRPORT FIRE DEPT CALLED AS PRECAUTION.  PLEASE NOTE THAT MANUFACTURER IS L HOTELLIER, LOUIS AND DOES NOT EXIST ON DROP-DOWN LIST. (TC# 20061110005)                                                                                                                                                                                                                                                     2L72 4F4  FRTA28NM   E37NE                
20080220000062008022000006WP  2008       2          20         CA061110006      120061109G5410C04623          FRAME                                   ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              NACELLE         BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       333                                                            (CAN) DURING INSPECTION FOR SB NR 59, C046-23 FOUND BROKEN AT THE EAR AS DESCRIBED IN THE SB PART, ON ORDER FOR REPLACEMENT AND A KIT KI-185 TO PREVENT VIBRATION OF THE TUBE WILL BE INSTALLED. FRAME WILL BE SENT TO MFG FOR EVALUATION IAW THEIR REQUEST.  (TC NR 20061110006)                                                                                                                                                                                                                                                                                                                                                                                                                                                               1G71 3O3  O  H11NM   1E4                  
20061205002242006120500224WP  2006       12         5          CA061110007      220061026G7250TFE73120BR      ENGINE                                  LEAR  45    45LEAR      5170805CE  GARRTTTFE731TFE7312     01518WP                                              FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                          P116549C                    (CAN) DURING POST/PREFLIGHT INSPECTION MAINTENANCE PERSONNEL NOTICED NICKS ON 2 OF THE THE THIRD STAGE TURBINE BLADES.  ENGINE HAS BEEN REMOVED AND SENT TO AN HEAVY MAINTENANCE FACILITY FOR INVESTIGATION AND REPAIR. A RENTAL ENGINE HAS BEEN INSTALLED AND THE AIRCRAFT RETURNED TO SERVICE  (TC# 20061110007)                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F4  FRTT00008WIE6WE                 
20070126003232007012600323NE  2007       1          26         CA061113001      220061105G7200PT6AD           ENGINE                                  BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE  HARTZLHCE4A HCE4A3I     NE                  MALFUNCTIONED   W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         O  OTHER                                                                         CLCLIMB          1                      CA                                                                      (CAN) .5 HRS AFTER A SCHEDULED REPLACEMENT OF THE NR 3 AND NR 4 BEARING ASSY AND THE NR 1 AND NR 2 POWER TURBINE DISC`S DUE TO CYCLE LIFE LIMIT BEING REACHED, THE ENGINE LOST OIL PRESSURE AND WAS SHUTDOWN AND AIRCRAFT RETURNED TO DEPARTURE FIELD WITHOUT FURTHER INCIDENT. AWAITING TEAR DOWN REPORT FOR ADDITIONAL DETAILS. (TC NR 20061113001)                                                                                                                                                                                                                                                                                                                                                                                           2L72 4T4  TRTA24CE   E26NE   5  CP10NE    
20061205000642006120500064EU  2006       12         5          CA061114001      320061113G6197697070212       BUSS BAR                                BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R4304 R4304*      EU  PROPELLER ASSY  CHAFED          W      E   ENGINE SHUTDOWN                                                                                 FJ FLT CONT AFFECTED         WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) NO.1 ENGINE SHUTDOWN MANUALLY IN FLT DUE PEC FAIL CAUTION AND PROP SPEED AT 1060 RPM. FAULT CODES LH CH A/B 160 AND 162. MAINT DISPATCHED TO T/S. FOUND BUSBAR FOR PROPELLER DEICE CHAFING ON MPU BRACKET, CAUSING MPU TO PICKUP SENS FROM BUSBAR. MPU ADJUSTED AND NEW BUSBAR INSTALLED.  ENGINE GROUND RUNS C/O NORMAL. (TC# 20061114001)                                                                                                                                                                                                                                                                                                                                                                                               2H72 4T4  TRTA13NM   E00062EN6  CP890     
20061205000722006120500072EU  2006       12         5          CA061114003      120061107G783032143304        SHUTOFF VALVE                           AIRBUS310   A310304     3930339EU  GE    CF6   CF680C2*         GL                              THRUST REVERSER LEAKING         W      C   ABORTED TAKEOFF                                                                                 J  WARNING INDICATION                                                            TOTAKEOFF        1                      CA                  AEX10603                                            (CAN) DURING TAKE OFF AT APPROXIMATELY 100 KNOTS NR 1 ENGINE THRUST REVERSER UNLOCKED LIGHT ILLUMINATED ACCOMPANIED WITH EAM MESSAGE NR 1 ENG REV UNLOCK. THE FLIGHT CREW REJECTED THE TAKE OFF ROLL, CYCLED THE REVERSER WITH NO FAULTS. CREW THEN ELECTED TO RETURN TO GATE. TO AVOID FURTHER DELAY, THE REVERSER WAS DEACTIVATED AND THE FLIGHT WAS DISPATCHED UNDER MEL. DURING TROUBLE SHOOTING FOUND THE PRESSURE REGULATING AND SHUT OFF VALVE BYPASSING. PRESSURE REGULATING/SHUT OFF VALVE REPLACED AND SYSTEM TESTED SERVICEABLE.                                                                                                                                                                                                    2L72 4F4  FRTA35EU   E23EA                
20070126003302007012600330CE  2007       1          26         CA061114005      120061110G2730656530128       GUARD                                   CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              ELEVATOR        CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) WHILE COMPLYING WITH COMPANY CAMPAIGN NOTICE CN 851-27-20-035, BOTH ELEVATOR CABLE GAURDS WERE FOUND CRACKED ADJASENT TO THE CLAMPS. THE TUBES WERE FOUND WITH .5 INCH LONGITUDINAL CRACKS. ADDITIONALLY ONE OF THE ATTACH CLAMPS WAS FOUND TO HAVE THE WRONG PN MS 21919WH10 INSTEAD OF MS 21919WDG10. MAINTENANCE ENTRIES WERE MADE WITH RESPECT TO THE WORK ACCOMPLISHED IN THE CONDITION AND CORRECTION SHEET ASD MP-01-860-10-30-01. (TC NR 20061114005)                                                                                                                                                                                                                                                                             1L72 4F4  F  A22CE   E1NE                 
20061205000662006120500066EU  2006       12         5          CA061114006      120061112G2150                A/C PACK                                AIRBUS310   A310304     3930339EU  GE    CF6   CF680C2*         GL                              NR 2            ODOR            W      A   UNSCHED LANDING                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      CLCLIMB          1                      CA                                                                      (CAN) IN CLIMB OUT ECAM WARNING MIN EQUIPMENT BAY SMOKE CAME ON WITH BURNING ODOR AND A SMALL AMOUNT OF SMOKE IN THE FLIGHT DECK AND FWD CABIN. AIRCRAFT RETURNED TO THE STATION. MAINTENANCE INSPECTED THE MIN EQUIPMENT COMPARTMENT (NO FINDING). DURING ECS COMPARTMENT INSPECTION FOUND A BOOT LEAKING ON NR 2 PACK HEAT EXCHANGER WITH A BURNING ODOR COMING OUT OF THE PACK. NR 2 ENGINE BLEED AND NR 2 PACK DEACTIVATED AND RELEASE UNDER MEL. GROUND RUN PERFORMED WITH NR 1 SYSTEM AND NO FURTHER WARNING AND BURNING ODOR. DURING INVESTIGATION THE BROKEN BOOT COUPLING WAS REPLACED ON NR 2 PACK. THE AIR-COOLING SYSTEM WAS CLEANED AS PER M/M AND NR 2 COALESCOR BAG WAS REPLACED. SYSTEM WAS  GROUND CHECKED SERVICEABLE.        2L72 4F4  FRTA35EU   E23EA                
20070126003352007012600335SO  2007       1          26         CA061114007      120061110G7603454253          THROTTLE CABLE                          PIPER PA31  PA31325     7103105SO  LYC   O540  TIO540F2BD  41532EA  HARTZLHCE3Y HCE3YR2A    GL  COCKPIT         FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA                                                                      (CAN)  RT ENGINE THROTTLE CABLE FAILURE:  DURING A ROUTINE FLIGHT, THE PILOT, ENROUTE , NOTED THAT THE RT ENGINE THROTTLE CONTROL WAS STIFF ON APPROACH. THE AIRCRAFT EXPERIENCED A NORMAL LANDING, ONCE ON THE GROUND THE PILOT REPORTED THAT THE RT ENGINE WAS RUNNING AT IDLE AND WOULD NOT RESPOND TO THROTTLE MOVEMENTS. THE AIRCRAFT WAS TAXIED TO THE RAMP AND SHUTDOWN.  THE RT ENGINE WAS INSPECTED, AND MAINTENANCE DETERMINED THE RT THROTTLE CABLE IN THE CABIN PEDESTAL HAD FAILED. THE THROTTLE CABLE WIRES HAD SEVERED APPROXIMATELY .2500 FROM THE SWAGED PORTION OF THE ROD END. UNFORTUNATELY ON A ROUTINE INSPECTION THIS PORTION OF THE CABLE IS COVER BY THE CABLE SLEEVE AND CANNOT BE INSPECTED.   THE RT ENGINE THROTTLE1L72 3O3  O  A20SO   E14EA   5  CP33EA    
20061205001852006120500185NM  2006       12         5          CA061114008      120061101G561058935734        WINDOW                                  BOEING737   7377CG      13844FANM  CFMINTCFM567CFM567B22   13802NE                              COCKPIT         FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA       10744                                                          (CAN) ON NOV. 1, 2006 A/C 216 EXPERIENCED A CRACKED NR 4 RT EYEBROW WINDOW. THE A/C CONTINUED TO ITS DESTINATION WITHOUT ANY FURTHER EVENTS. THE NR 4 WINDOW WAS REPLACED.BOEING IS AWARE OF THIS IN SERVICE ISSUE AND HAS INITIATED SERVICE RELATED PROBLEM (SRP) 56-0018. BOEING HAS ALSO ISSUED SERVICE BULLETIN 737-56-1017 TO PROVIDE 737NG OPERATORS WITH AN OPTION TO REPLACE THE NR 4 AND 5 WINDOWS WITH STRUCTURAL PLUGS. WESTJET IS PLANNING ON INCORPORATING THIS SERVICE BULLETIN.                                                                                                                                                                                                                                                  2L72 4F4  FRTA16WE   E00055EN             
20061205002192006120500219NM  2006       12         5          CA061114009      120061027G561058935733        WINDOW                                  BOEING737   7377CG      13844FANM  CFMINTCFM567CFM567B22   13802NE                              COCKPIT         CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA       14236                                                          (CAN) ON OCT. 27, 2006 A/C 201 EXPERIENCED A CRACKED NR 4 LT EYEBROW WINDOW. THE A/C CONTINUED TO ITS DESTINATION WITHOUT ANY FURTHER EVENTS. THE NR 4 WINDOW WAS REPLACED.  BOEING IS AWARE OF THIS IN SERVICE ISSUE AND HAS INITIATED SERVICE RELATED PROBLEM (SRP) 56-0018. BOEING HAS ALSO ISSUED SERVICE BULLETIN 737-56-1017 TO PROVIDE 737NG OPERATORS WITH AN OPTION TO REPLACE THENR 4 AND 5 WINDOWS WITH STRUCTURAL PLUGS. WESTJET IS PLANNING ON INCORPORATING THIS SERVICE BULLETIN.  (TC# 20061114009)                                                                                                                                                                                                                             2L72 4F4  FRTA16WE   E00055EN             
20061205001912006120500191NM  2006       12         5          CA061114010      120061031G561058935733        WINDOW                                  BOEING737   7377CG      13844FANM  CFMINTCFM567CFM567B22   13802NE                              COCKPIT         FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA       14250                                                          (CAN) ON OCT. 31, 2006 A/C 202 EXPERIENCED A CRACKED NR 4 LT EYEBROW WINDOW. THE A/C CONTINUED TO ITS DESTINATION WITHOUT ANY FURTHER EVENTS. THE NR 4 WINDOW WAS REPLACED. BOEING IS AWARE OF THIS IN SERVICE ISSUE AND HAS INITIATED SERVICE RELATED PROBLEM (SRP) 56-0018. BOEING HAS ALSO ISSUED SERVICE BULLETIN 737-56-1017 TO PROVIDE 737NG OPERATORS WITH AN OPTION TO REPLACE THE NR 4 AND 5 WINDOWS WITH STRUCTURAL PLUGS. WESTJET IS PLANNING ON INCORPORATING THIS SERVICE BULLETIN.                                                                                                                                                                                                                                                2L72 4F4  FRTA16WE   E00055EN             
20061205000812006120500081NM  2006       12         5          CA061114011      120061106G561058935841        WINDOW                                  BOEING737   73776N      13844CHNM  CFMINTCFM567CFM567B22   13802NE                              COCKPIT         CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA       13936                                                          (CAN) ON NOV. 6, 2006 A/C 011 EXPERIENCED A CRACKED NR 5 LT EYEBROW WINDOW. THE A/C CONTINUED TO ITS DESTINATION WITHOUT ANY FURTHER EVENTS. THE NR 5 WINDOW WAS REPLACED.BOEING IS AWARE OF THIS IN SERVICE ISSUE AND HAS INITIATED SERVICE RELATED PROBLEM (SRP) 56-0018. BOEING HAS ALSO ISSUED SERVICE BULLETIN 737-56-1017 TO PROVIDE 737NG OPERATORS WITH AN OPTION TO REPLACE THE NR 4 AND 5 WINDOWS WITH STRUCTURAL PLUGS. WESTJET IS PLANNING ON INCORPORATING THIS SERVICE BULLETIN.                                                                                                                                                                                                                                                  2L72 4F4  FRTA16WE   E00055EN             
20070126003412007012600341EA  2007       1          26         CA061114012      120061114G26122155101681      BRACKET                                 CNDAIRCL215 CL2151A10   1900320EA  PWA   R1340 CWASP       52016NE  HAMSTD43E   43E60       NE  FIRE WARNING    CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING INSPECTION OF PN 215-51016-816 RELAY BRACKET ASSY, (IPC 26-10-00 FIG 2 PAGE 4) 3 OF THE RELAY BASES (ITEM 35) WERE FOUND CRACKED. THE MOUNTING HARDWARE (ITEM 36) WAS INCORRECT FROM NEW, ACCORDING TO THE DIAGRAM AND INCOMPATIBLE WITH THE RELAYS, 4 OF ON THIS ASSY. 2 OTHER AIRCRAFT WERE INSPECTED  AND ONE RELAY BASE WAS FOUND CRACKED ON EACH OF THEM. THESE RELAYS ARE PART OF THE FIRE WARNING, LANDING GEAR INDICATION AND WATER DOOR SYSTEM. THE RELAY BASES WILL BE REPLACED WITH SERVICEABLE UNITS. WE WOULD LIKE TO SUGGEST OTHER OPERATORS INSPECT THESE RELAY BASES FOR CRACKS. (TC NR 20061114012)                                                                                                               2H72 4R3  RRTA14EA   ATC14   6  CP871     
20070125001182007012500118SO  2007       1          25         CA061115001      220061115G8500                UNKNOWN                                 DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO  SNSNCHW69EK W69EK63     EA  ENGINE          UNKNOWN         W      D   RETURN TO BLOCK                                                                                 R  PARTIAL RPM/PWR LOSS                                                          TXTAXI/GRND HDL  1                      CA       138                                                            (CAN) REPORTED DEFECT, ON APPLICATION OF FULL POWER, ENGINE WOULD ALMOST CUT-OUT, THEN CATCH AND ACHIEVE FULL POWER. THE AIRCRAFT HAD PREVIOUSLY BEEN SNAGGED FOR QUITING SHORTLY AFTER LANDING, ON OCT. 17TH, AT WHICH TIME THE FUEL SYSTEM HAD BEEN INSPECTED, AND ADJUSTED IAW SID 97-3C AND RELEASED. THEREFORE MFG WAS CONTACTED AND ELECTED TO SEND A TECH REP TO OUR FACILITIES AND REPLACED MECHANICAL FUEL PUMP, THROTTLE BODY, FUEL MANIFOLD, WITH NEW UNITS. COMPLETE FUEL SYSTEM WAS FLUSHED AND FUEL INJECTOR NOZZLES CLEANED. FUEL SYSTEM SET UP IAW SID97-3C AND AIRCRAFT RELEASED. (TC NR 20061115001)                                                                                                                          1L71 3O3  ONTTA4CH   E7SO    5  NTA4CH    
20061213000752006121300075    2006       12         13         CA061115002      120060616G61208210263         CSD                                                                        GARRTTTFE731TFE731*     01518WP                              PROPELLER       MAKING METAL    W      O   OTHER                                                                                           J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      CA                                                                      (CAN) S/N 2479220  UNIT OVERHAULED AT MFG. UNIT WAS INSTALLED ON ENGINE IN A TEST CELL AND WAS RETURNED WITH TSO: 0.0 AND REPORTED SNAG OF RESET PRESSURE TOO LOW, PART REJECTED.  AFTER DISASSEMBLY AT OUR FACILITY IT WAS NOTICED THAT THE INTERNAL SHAFT ASSEMBLY WAS SCORING THE HOUSING, MAKING METAL AND PROGRESSING TOWARD SEIZURE AND POSSIBLE SHAFT SHEARING. ALTHOUGH THE CAUSE HAS NOT BEEN DETERMINED, OIL STARVATION IS SUSPECTED.  UNIT HAS BEEN SENT TO (OEM) FOR A LABORATORY INVESTIGATION TO DETERMINE THE FAILURE ROOT CAUSE. RESULTS OF THE INVESTIGATION WILL FOLLOW.  (TC NR 20061115002)                                                                                                                                        4  F          E6WE                 
20061205000672006120500067EU  2006       12         5          CA061115004      120061112G3230005LG005B       CONTROL UNIT                            AIRBUS330   A330243     3930330EU                                                               MLG             MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA       16519                                                          (CAN) DURING CLIMB, CREW RETRACTED THE LANDING GEAR AND THE LEFT HAND GEAR UNLOCK LIGHT REMAINED ILLUMINATED ALONG WITH ASSOCIATED ECAM NR 1 SYSTEM LT GEAR TRIANGLE AND INTERMITTENT NOSE GEAR UNLOCK LIGHT. THE FLIGHT CREW ELECTED TO DIVERT INTO A MAIN MAINTENANCE BASE FOR RECTIFICATION OF THE FAULT. RECTIFICATION; NR 1 LGCIU REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F    RTA46NM                        
20061205000792006120500079WP  2006       12         5          CA061115005      220061106G7314307085063       PUMP                                    LEAR  35    35LEAR      5170600CE  GARRTTTFE731TFE731*     01518WP                              LT ENGINE FUEL  FAILED          W      C   ABORTED TAKEOFF                                                                                 XJ ENGINE FLAMEOUT           WARNING INDICATION                                  TOTAKEOFF        1                      CA       9218                                                           (CAN) AIRCRAFT WAS CLEARED FOR T/O.  POWER WAS ADVANCED TO 93.5% N1 ON BOTH ENGINES.  APPROXIMATELY 1 SECOND LATER LT ENGINE FAILED.  T/O WAS REJECTED.  AME TROUBLESOT THE SNAG AND DISCOVERED THAT THE LT ENGINE FUEL PUMP PRESSURE WAS NOT WITHIN ACCEPTABLE LIMITS.  FUEL PUMP AND FUEL CONTROL UNIT REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F4  F  A10CE   E6WE                 
20070125001192007012500119SO  2007       1          25         CA061115006      120061114G55114653003         RIB                                     PIPER PA31T PA31T       7103124SO  PWA   PT6   PT6A28           EA  HARTZLHCB3T HCB3TN3     GL  HORIZONTAL STAB CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       407                                                            (CAN) DURING AN EVENT NR 1 INSPECTION THE LT HORIZONTAL STABILIZER OB RIB WAS FOUND CRACKED WHERE THE ELEVATOR OB HINGE ATTACH POINT IS.  THE RIB WAS REPLACED. (TC NR 20061115006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L72 3T4  T  A8EA    E4EA    6  CP15EA    
20070125001212007012500121SW  2007       1          25         CA061115007      120061101G5330                SKIN                                    BELL  206   206B        1181511SW  ALLSN 250C  250C20B     03013GL                              FUSELAGE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       14725                                                          (CAN) DURING SCHEDULED MAINTENANCE, IN COMPLIANCE WITH CF-91-35 (CABIN ROOF BOXBEAM INSPECTION),  A CRACK WAS DISCOVERED IN THE BOXBEAM LOWER SKIN ORIGINATING FROM AN INSPECTION PANEL CUT-OUT RIVET HOLE.  THIS SKIN WAS CRACKED ACROSS THE RIVET HOLE ABOUT 1.25 INCHES IN EACH DIRECTION. (TC NR 20061115007)                                                                                                                                                                                                                                                                                                                                                                                                                               1G71 3U3  U  H2SW    E4CE                 
20061205000712006120500071EA  2006       12         5          CA061116001      120061109G5610NP1393226       WINDOW                                  CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              COCKPIT         CRACKED         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      CA       11003                                                          (CAN) AIRPLANE DIVERTED FOUND:  RT SIDE-WINDOW CRACKED. RT SIDE WINDOW REMOVED ACC.AMM.  RT SIDEWINDOW INSTALLED ACC AMM 56-12-01-400-801.  CABIN PRESS TEST PERF,. OK                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA21EA   E15NE                
20061205000782006120500078EA  2006       12         5          CA061116002      120061106G5610NP139321002     WINDSHIELD                              CNDAIRCL600 CL6002C10   1390015EA  GE    CF34  CF348C1          NE                              COCKPIT         CRACKED         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) NOTIFED BY SOC (OPERATIONS) THAT AIRCRAFT WAS DIVERTING TO IND DUE TO CAPT FWD WINDSHIELD CRACKED AT 39,000 FEET ON OUTER PLY. C/A - RAR CAPT W/S IAW CRJ 700 AMM 56-11-01 OPS CHECK LEAK CHECK GOOD.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F4  FRTA21EA   EOOO63EN             
20061205000572006120500057EA  2006       12         5          CA061116003      120061116G5712600911545       BULKHEAD                                CNDAIRCL600 CL600*             EA  GE    CF34  CF343A      30015NE                              BS 559          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) BULKHEAD STRUCTURE AT STATION 559.00 CRACKED ON TWO AILERON MIXER  (P/N 600-91154-5)  ATTACHMENTS BOLTS. A/C HOURS:25688 A/C CYCLES:30488                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA21EA   E15NE                
20061205000692006120500069EU  2006       12         5          CA061116004      120061110G2497                CABLE                                   AEROSPATR42 ATR42300    8680920EU  PWA   120   PW120            NE  HAMSTD14SF  14SF5       NE  DC GENERATOR    ARCED           W      O   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      TXTAXI/GRND HDL  1                      CA                                                                      (CAN) ON START UP THE NR 2 STARTER GENERATOR `PLUS` CABLE ARCED THROUGH A FEW INCHES FROM THE CONNECTION AT THE STARTER.THE CABLE WAS COMPLETELY SEVERED AND THE ADJACENT CONDUCTORS WERE DAMAGED. THE NR 2 GENERATOR, AFFECTED CONDUCTORS AND THE INVERTER WERE REPLACED AND THE AIRCRAFT RETURNED TO BASE WHERE ADDITION ASSESSMENT IS ON GOING.                                                                                                                                                                                                                                                                                                                                                                                              2H72 4T4  TRTA53EU   E20NE   6  CP7NE     
20061205000622006120500062NM  2006       12         5          CA061116005      120061113G75408209074         SWITCH                                  BOMBDRDHC8  DHC8402     1390042NM                                                               RT NACELLE      FAILED          W      D   RETURN TO BLOCK                                                                                 J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      CA       135  135                                                       (CAN) BLEED HOT CAUTION NR 2 CAME ON. CDS INTEREGATION FAULT CODE 1701. RIGHT BLEED OVERTEMPERATURE SWITCH FLAGGED. REPLACE SWITCH.  SERIAL NUMBER 0781.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2H72 4T    RTA13NM                        
20070125001242007012500124CE  2007       1          25         CA061116006      120061116G53301014302051      SKIN                                    BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA  HARTZLHCB3T HCB3TN3     GL  BS 251          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) CABIN BOTTOM SKIN FOUND CRACKED ADJACENT TO ROTATING BEACON DOME MOUNTING. REPAIR DRAWING REQUESTED. (TC NR 20061116006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L72 4T4  T  A24CE   E4EA    6  CP15EA    
20070125001272007012500127SW  2007       1          25         CA061117001      120061103G73342060615357      TRANSDUCER                              BELL  206   206L        1181522SW  ALLSN 250C  250C20R2         GL                              FUEL PRESSURE   READS LOW       W      K   NONE                                                                                            N  FALSE WARNING                                                                 ININSP/MAINT     1                      CA                                                                      (CAN) UNDER READING FUEL PRESSURE. REMOVED AND INSTALLED REPLACEMENT PRESSURE TRANSDUCER PN BSE 206-30G SN2617-1-251 (TC NR 20061117001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1G71 3U3  U  H2SW    E4CE                 
20080306002732008030600273SO  2008       3          6          CA061117002      220060921G85604707829003R     CONTROLLER                              CESSNA206   TU206A      2073318CE  CONT  O520  TSIO520C    17040SO  HARTZLHCC3Y PHCC3YF1    GL  OIL PRESSURE    FAILED          W      C   ABORTED TAKEOFF                                                                                 R  PARTIAL RPM/PWR LOSS                                                          TOTAKEOFF        1                      CA            1350                                                      (CAN) ERRATIC MANIFOLD PRESSURE DUE TO CONTROLLER FAILURE TO REGULATE OIL PRESSURE FROM WASTEGATE (TC NR 20061117002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1H71 3O3  O  A4CE    E8CE    5  CP25EA    
20070808001222007080800122CE  2007       8          8          CA061117003      120061116G57538005T20062      DOUBLER                                 CESSNA340   340A        2076405CE  CONT  O520  TSIO520NB   17040SO  MCAULY3AF34C3AF34C*     GL  TE FLAP         MISINSTALLED    W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA       1324                                                           (CAN) DURING A ROUTINE INSPECTION, DISCOVERED LT AND RT WING RIBS AT STA 117.48 TO BE CONFLICTING WITH THE RIB AT SIMILAR LOCATION WHEN FLAPS ARE RETRACTED.  AFTER INSPECTION, FOUND THAT THE SPOILER DOUBLER INSTALLED IN 1995 WAS THE WRONG DIMENSION ALLOWING WING RIB TO BE POSITIONED INCORRECTLY.   ON FURTHER INVESTIGATION FOUND THE TEMPLATE NR 8005T AND THE INSTALLATION INSTRUCTIONS NR SP8000 SUPPLIED WITH THE STC SA4948NM TO BE CONTRADICTING EACH OTHER IN RESPECT TO THE NEW LOCATION OF THE WING RIB.  IF ONE OF THE FLAPS BECAME INOPERATIVE DUE TO THE FACT THAT THE RIBS HOOKED ON EACH OTHER. (TC NR 20061117003)                                                                                                       1L72 3O3  O  3A25    E8CE    5  CP22EA    
20061205000842006120500084EA  2006       12         5          CA061117004      220061104G8530SL36006WA1      CYLINDER HEAD                           BEECH 95    95          1153402CE  LYC   O360  IO360B1B    41514EA                              ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1989                                                           (CAN) DURING A ROUTINE 100 HOUR INSPECTION A CRACK WAS FOUND ON THE RH ENGINE #4 CYLINDER STARTING AT THE TOP SPARK PLUG HOLE AND CONTINUING DOWN TO THE EXHAUST PORT. THE CYLINDER WAS REMOVED AND REPLACED. (TC# 20061117004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1L72 3O3  O  3A16    1E10                 
20061205000822006120500082NM  2006       12         5          CA061117005      120061106G322069601002        SUPPORT                                 BOEING737   737200      1384453NM  PWA   JT8   JT8D17      52049NE                              MLG             CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA                                                                      (CAN) ON WALK AROUND AFTER LANDING FOUND CENTER SUPPORT ASSY OF GRAVEL DEFLECTOR CRACKED.  CENTER SUPPORT ASSY CRACK REPAIRED.  ASSEMBLY SUPPORT FITTING P/N69-60100-2 REPLACED AIRCRAFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  F  A16WE   E2EA                 
20061205000632006120500063EA  2006       12         5          CA061117006      120061113G499038004882        APU                                     CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                                              OVERSERVICED    W      O   OTHER                                                                                           BJ SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION                                  DEDESCENT        1                      CA       1787717877                                                     (CAN) APPROXIMATELY 10 MINUTES FROM DESTINATION, AIRCRAFT DECLARED AN EMERGENCY DUE TO SMOKE IN THE LAVATORY. AIRCRAFT WAS DESCENDING THROUGH 5,000 FT WHEN THE BLEEDS WERE SWITCHED FROM ENGINES TO APU. WITHIN A SHORT PERIOD OF TIME A BURNT OIL SMELL WAS OBSERVED IN THE CABIN, AND THE LAV SMOKE DETECTOR WAS GOING OFF. THE CREW ALSO RECEIVED A "TOILET SMOKE" CAUTION MESSAGE. CREW REQUESTED EMERGENCY SERVICES BE ALERTED FOR ARRIVAL. SHORTLY THEREAFTER THE SMOKE INDICATION WENT OUT. FLIGHT LANDED SAFELY. MAINTENANCE INVESTIGATED AND FOUND THE APU OVER SERVICED. EXCESS OIL WAS DRAINED TO AN ACCEPTABLE LEVEL, AND LT & RT COALESCER BAGS P/N 753689-3 REPLACED IN ACCORDANCE WITH THE AMM 21-51. AIRCRAFT WAS THEN RUN ON A2L72 4F4  FRTA21EA   E15NE                
20070808001232007080800123EU  2007       8          8          CA061117007      120061102G8011A2042C          PDU                                     SAAB  SF340 SF340A      7850100EU  GE    CT7TP CT75A2      30030NE  ROTOL R389  R3894123F25 NE  LT START RELAY  FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                              340A019                                 (CAN) WHEN GROUND POWER WAS ATTACHED TO THE AIRCRAFT THE LT ENGINE BEGAN AN UNCOMMANDED START SEQUENCE.  THE FAULT WAS TRACED TO THE LT STARTER RELAY CONTACTS LOCATED IN THE LT POWER DISTRIBUTION UNIT (PDU).  THE PDU WAS REPLACED AND THE AIRCRAFT OPERATED NORMALLY. (TC NR 20061117007)                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4T4  TRTA52EU   E8NE6   6  CP30NE    
20061205000552006120500055NE  2006       12         5          CA061118001      220061117G7230                ENGINE                                  CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30015NE                              NR 1            BIRD INGESTION  W      A   UNSCHED LANDING                                                                                 CEJF.O.D.                    VIBRATION/BUFFET          WARNING INDICATION        CLCLIMB          1                      CA                                                                      (CAN) AFTER GEAR-UP SELECTION THE AIRCRAFT ENCOUNTERED A VIBRATION, FELT THROUGHOUT ENTIRE PLANE,THAT WOULD INCRESE/DECREASE WITH THROTTLE MOVEMENT. AIRCRAFT RETURNED TO THE ORIGINATING DEPARTURE STATION AND LANDED SAFELY. MAINTENANCE FOUND NR 1 ENGINE FAN BLADES DAMAGED & BIRD REMAINS ON OIL COOLER, DUE TO A LARGE BIRD INGESTION.                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F4  FRTA21EA   E15NE                
20070125001292007012500129SW  2007       1          25         CA061120001      120061104G7333205061635005    SWITCH                                  BELL  206   206L        1181522SW  ALLSN 250C  250C20R2         GL                              FUEL FLOW       LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) REMOVED LT FUEL FLOW SWITCH DUE TO LEAKING. INSTALLED FUEL FLOW SWITCH PN 205-061-635-005 SN 9607 (TC NR 20061120001).                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1G71 3U3  U  H2SW    E4CE                 
20070125001312007012500131SO  2007       1          25         CA061120002      220060930G73235038901029      GOVERNOR                                BEECH 58    58          1152740CE  CONT  O550  IO550C           SO                              ENGINE          SEPARATED       W      A   UNSCHED LANDING                                                                                 F  FLT CONT AFFECTED                                                             LDLANDING        1                      CA       1121                                                           (CAN) SNAS: ENGINE GOVERNOR CONTROL NO RESPONSE. FOUND LT GOVERNOR CABLE END, SEPARATE FROM CRIMPED END FILET ATTACHED TO ROD END. (TC NR 20061120002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1L72 3O3  O  3A16    E3SO                 
20070125001322007012500132SO  2007       1          25         CA061120003      120061115G270062701153        CONTROL CABLE                           PIPER PA44  PA44180     7104402SO  LYC   O360  O360E1A6    41514EA  HARTZLHCC2Y HCC2YR2     GL  STABILATOR      SEVERED         W      A   UNSCHED LANDING                                                                                 F  FLT CONT AFFECTED                                                             CRCRUISE         1                      CA                                                                      (CAN) PILOT REPORTED LOSS OF EFFECTIVE ELEVATOR CONTROL DURING ROUTINE TRAINING FLIGHT. AIRCRAFT RETURNED TO BASE WITH STABILATOR CONTROL MANAGED MAINLY BY STABILATOR TRIM SYSTEM. AIRCRAFT LANDED SAFELY.  INITIAL INSPECTION OF STABILATOR SYSTEM CONFIRMED LIMITED RESPONSE TO CONTROL YOKE MOVEMENT.  FURTHER INSPECTION OF CABLES REVEALED THAT THE SWAGED END OF THE AFT LOWER CABLE WAS BROKEN AND SYSTEM WAS HELD TOGETHER BY TURNBUCKLE SAFETY LOCK WIRE. AFFECTED CABLE HAS BEEN REMOVED FOR FURTHER INSPECTION AND REPLACEMENT.  CABLE DEFECT LOCATED BETWEEN FUSELAGE STA: 156.00 AND 191.00. PART TOTAL TIME IS UNKNOWN.  AIRCRAFT TOTAL TIME IS 6593.3 HRS. (TC NR 20061120003)                                                  1L72 3O3  O  A19S0   E286    5  CP920     
20061205000372006120500037NE  2006       12         5          CA061120005      220061119G72304114T15P02      FAN BLADE                               CNDAIRCL600 CL600*             EA  GE    CF34  CF348E5     30015NE                              ENGINE          BENT            W      O   OTHER                                                                                           C  F.O.D.                                                                        APAPPROACH       1                      CA       4477 182                           194301                      (CAN) ON APPROACH CREW SAW LARGE WHITE BIRD , FELT AND HEARD THUMP ON LEFT SIDE OF AIRCRAFT. MAINTENANCE INSPECTION FOUND #1 ENGINE INLET BYPASS FAN BLADES POSITIONS 1 THRU 5 DAMAGED AND BENT. BORESCOPE OF ENGINE COMPRESSOR FOUND NO OTHER DAMAGE. AIRCRAFT WILL BE RETURNED TO SERVICE AFTER BLADE REPLACEMENT AND SATISFACTORY GROUND RUNS. (TC# 20061120005)                                                                                                                                                                                                                                                                                                                                                                             2L72 4F4  FRTA21EA   E00063EN             
20080124003212008012400321SW  2008       1          24         CA061120006      120061120G272041621L          RUDDER PEDAL                            BBAVIA7     7GCBC       1220601SW  LYC   O320  O320A2D     41508EA  SNSNCH74D   74DM        EA  COCKPIT         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1739                                                           (CAN) DURING REPLACEMENT OF THE FUEL SHUTOFF VALVE THE LT FRONT RUDDER/BRAKE PEDAL WAS FOUND CRACKED BETWEEN THE BRAKE PEDAL UPRIGHT AND THE OB PEDAL HINGE. THE DEFECT APPEARS TO BE CAUSED BY BRAKING FORCES APPLIED BY THE FLIGHT INSTRUCTOR IN THE REAR SEAT, THE LINK ROD AND BELLCRANK ON THE FRONT PEDAL TWIST THE PEDAL TO ACTUATE THE MASTER CYLINDERS, LOCATED FORWARD OF THE FRONT PEDALS. THE TWISTING BENDS AND CRACKS THE PEDAL.     THIS IS THE OLD-STYLE PEDAL. THE NEWER STYLE IS PLATE-SHAPED RATHER THAN TEE-SHAPED AND SHOULD BE MORE RESISTANT TO THE TWISTING FORCES. (TC NR 20061120006)                                                                                                                                 1H71 3O3  ONCA759    E274    5  NP88614   
20070125001332007012500133EU  2007       1          25         CA061120007      120061117G6310350A35105901    COUPLING                                SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1        NE                              M/R DRIVESHAFT  CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING 1000 HR INSPECTION DISC COUPLING FOUND CRACKED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1G71 3U3  U  H9EU    E19EU                
20061205000562006120500056NE  2006       12         5          CA061120008      320061117G611178229911        SPACER          HAMSTD                  AEROSPATR42 ATR42300    8680920EU  PWA   120   PW120            NE  HAMSTD14SF  14SF5       NE  PROPELLER       TORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) PROPELLER BLADE INSPECTED AND FOUND TIGHT IN HUB. INVESTIGATION REVEALED PROP BLADE SPACER HAD FAILED. PROP BLADE REMOVED AND NEW SPACER INSTALLED. PROP BLADE REINSTALLED AND GROUND RUN CHECKED SERVICEABLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2H72 4T4  TRTA53EU   E20NE   6  CP7NE     
20061205000392006120500039NE  2006       12         5          CA061120009      220061118G7230652244143       DUCT                                    BOEING727   727223      1384074NM  PWA   JT8   JT8D9       52048NE                              13TH STAGE SADDLRUPTURED        W      E   ENGINE SHUTDOWN                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) ENROUTE TO DESTINATION, #2 ENGINE FIRE WARNING. CHECKLIST ACCOMPLISHED, ENGINE SHUTDOWN.  13TH STAGE SADDLE DUCT FOUND RUPTURED, REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC# 20061120009)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L73 4F4  F  A3WE    E2EA                 
20061205000352006120500035NE  2006       12         5          CA061121001      220061119G7200                ENGINE                                  AIRBUS310   A310304     3930339EU  GE    CF6   CF680C2A5        NE                              NR 2            FAILED          W      A   UNSCHED LANDING                                                                                 BJ SMOKE/FUMES/ODORS/SPARKS  WARNING INDICATION                                  CLCLIMB          1                      CA       259454946                          690285                      (CAN) AFTER TAKE OFF AND DURING LEVEL AT 40,000 FT CREW GOT ECAM MESSAGE MIN EQUIPMENT SMOKE  WITH OVERHEAD WITH OVERHEAD LIGHT ON AND ODOR IN THE CABIN AND COCKPIT. CREW DECIDED TO RETURN BACK TO THE AIRPORT. QRH PROCEDURES WERE FOLLOWED. BOROSCOPE CARRIED OUT ON BOTH ENGINES. FOUND EVIDENCE OF OIL IN NR 2 ENGINE COMPRESSOR. NR 2 ENGINE REPLACED.                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  FRTA35EU   E13NE                
20070125001352007012500135SW  2007       1          25         CA061121002      120060826G6320206040156101    MAGNETIC SEAL                           BELL  206   206B        1181511SW  ALLSN 250C  250C20      03013GL                              M/R GEARBOX     LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN)  MAIN ROTOR GEARBOX MAGNETIC SEAL HAS EXCESSIVE LEAKAGE FROM MAIN INPUT SEAL. (TC NR 20061121002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1G71 3U3  U  H2SW    E4CE                 
20061205000322006120500032NM  2006       12         5          CA061121003      120061120G572082920010255     LINE                                    DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  WING            SPLIT           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) WHILE CARRYING OUT ZONAL INSPECTION 263 AND 264, BOTH WING ROOT DRAIN LINES WERE FOUND BLOCKED AT THE BELLY DRAINS. THE ACCUMULATED WATER IN THE DRAIN LINE IN TURN FROZE AND SPLIT THE DRAIN LINE CAUSING PRESSURIZATION LEAK AND WATER AND SKYDROL TO LEAK IN THE BELLY. (TC# 20061121003)                                                                                                                                                                                                                                                                                                                                                                                                                                              2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20061205000312006120500031SW  2006       12         5          CA061122001      120061120G81204709549001      WASTEGATE VALVE                         RKWELL700   700         7630520SW  LYC   O540  TIO540R2AD  41532EA                                              FAILED          W      D   RETURN TO BLOCK                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA            2124                                                      (CAN) WHEN THE PILOTS APPLIED MAX POWER FOR TAKE-OFF THE LH ENGINE WOULD ONLY PRODUCE 30 INCHES M.P.  THE TAKE-OFF WAS STOPPED AND THE AIRCRAFT RETURNED TO CHALKS. AFTER FOUND NO FAULTS. THE TURBO WHEEL WAS ABLE TO TURN FREELY. THE WASTE GATE WAS CHANGED OUT. REMOVED S/N WC-60101 AND INSTALLED S/N ML0144. THE AIRCRAFT WAS GROUND RUN AND THE MANIFOLD PRESSURE WAS AT MAX 44 INCHES AS REQUIRED. SYSTEMS CHECKED SERVICEABLE. (TC# 20061122001)                                                                                                                                                                                                                                                                                       1L72 3O3  O  A12SW   E14EA                
20070125001362007012500136SW  2007       1          25         CA061122002      120061103G243503600923        BEARING                                 BELL  206   206B        1181511SW  ALLSN 250C  250C20      03013GL                              STARTER GEN     FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       167  167   13955                                               (CAN) CUSTOMER REPORTED BEARING FAILURE ON MAIN SHAFT OF STARTER/GENERATOR.  BEARING CAGE CAME APART.  UPON INSPECTION.  IT WAS FOUND THE BEARING CAGE WAS NON-EXISTANT.  WE CONTACTED OUR SUPPLIER. (TC NR 20061122002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1G71 3U3  U  H2SW    E4CE                 
20070125001422007012500142SO  2007       1          25         CA061122003      120061121G30972937102         TERMINAL                                PIPER PA31T PA31T       7103124SO  PWA   PT6   PT6A28           EA  HARTZLHCB3T HCB3TN3     GL  DE ICE SYSTEM   BURNED          W      O   OTHER                                                                                           L  NO TEST                                                                       CRCRUISE         1                      CA                                                                      (CAN) PILOT REPORTED PROP AND ENGINE INLET BOOTS DE-ICE SYSTEM U/S ON LT ENGINE. SYSTEM HAS BEEN INSPECTED. FOUND NO POWER FROM CB TO MAIN POWER RELAY. PLATE ASSEMBLY CIRCUIT PROTECTOR FORWARD MOUNTING LT REMOVED AND DISCOVERED THAT WIRE FROM CB BURNED OUT AT TERMINAL CONNECTION DUE OVERHEAT OF TERMINAL. OVERHEATING OF TERMINAL APPEARED TO BE DUE CORROSION OF TERMINAL AND LOST OF CONDUCTIVITY THAT INCREASE THE RESISTANCE AND GENERATE ADDITIONAL HEAT. (TC NR 20061122003)                                                                                                                                                                                                                                                      1L72 3T4  T  A8EA    E4EA    6  CP15EA    
20061205000282006120500028NE  2006       12         5          CA061122004      220061122G7250                GAS GENERATOR                                                              PWA   120   PW123D      52152NE                              ENGINE          CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) SEE REPORT ATTACHED REGARDING SMOKE IN THE EXHAUST DURING ENGINE SHUTDOWN.  ENGINE S/N AG0060 DISASSEMBLY OF ENGINE REVEALED LARGE AMOUNT OF COKED OIL IN THE TURBINE SUPPORT CASE (NR 5 BEARING VENT TUBE AREA), WHICH IS TYPICALLY INDICATIVE OF CRACKS IN THE NR 5 BEARING SUPPORT AREA OF THE GAS GENERATOR CASE. OIL FROM THESE CRACKS CONTAMINATED THE P3 AIR SYSTEM. (TC# 20061122004)                                                                                                                                                                                                                                                                                                                                                    4  T          E20NE                
20070125001442007012500144SO  2007       1          25         CA061122006      120061106G321167042013        TRUNNION                                PIPER PA44  PA44180     7104402SO  LYC   O360  LO360E1A6   41514EA  HARTZLHCC2Y HCC2YR2     GL  MLG             CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       8804                                                           (CAN) AT INSPECTION NOTICED CRACK RIGHT THROUGH TRUNNION ASSY 67042-013.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L72 3O3  O  A19S0   E286    5  CP920     
20061205000682006120500068    2006       12         5          CA061122007      420061111G34215040002902      INDICATOR                               BRAERO748   HS7482A     4231001EU  RROYCEDART  DART5342         EU                              COCKPIT         FAILED          W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA                                                                      (CAN) DEPARTING THE CAPT`S HORIZON FAILED DURING TAKE-OFF. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WITHOUT INCIDENT. MAINTENANCE REPLACED THE GYRO AND THE AIRCRAFT WAS RETURNED TO SERVICE. (TC# 20061122007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 3T4  T  A24EU   A196                 
20061205000302006120500030EA  2006       12         5          CA061122008      120061121G2750NA              FLAP SYSTEM                             CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              TE FLAPS        JAMMED          W      O   OTHER                                                                                           FJ FLT CONT AFFECTED         WARNING INDICATION                                  CLCLIMB          1                      CA       1072710727                                                     (CAN) DURING MISSED APPROACH WHEN FLAP RETRACTION SELECTED, FLAPS REMAINED AT FULL 45DEG EXTENSION. CREW RECEIVED FLAP FAIL MESSAGE. DUE TO WEATHER CONDITIONS AIRCRAFT DIVERTED TO ALTERNATE AIRPORT WITH FLAPS REMAINING EXTENDED AT 45DEG. IN-FLIGHT FLAP RE-SET PROCEDURE CARRIED OUT WITH NO SATISFACTORY RESULT. AIRCRAFT LANDED NORMALLY AT ALTERNATE AIRPORT. AFTER ARRIVAL ON GROUND AIRCRAFT ELECTRICAL POWERED DOWN AND THEN RE-POWERED. FLAP SYSTEM FUNCTIONED NORMALLY. AIRCRAFT POSITIONED TO MAINTENANCE BASE FOR FURTHER INVESTIGATION. (TC# 20061122008)                                                                                                                                                                       2L72 4F4  FRTA21EA   E15NE                
20070808001242007080800124EA  2007       8          8          CA061123001      120061123G249721551226808     WIRE                                    CNDAIRCL215 CL2151A10   1900320EA  PWA   R2800 CA3         52026NE  HAMSTD43E   43E60       NE  DC POWER SYS    CHAFED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DC OVERHEAD PANEL WIRES CHAFING ON AIRCRAFT STRUCTURE.  (TC NR 20061123001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2H72 4R4  RRTA14EA   E231    6  CP871     
20061205000232006120500023NE  2006       12         5          CA061123002      220061123G7200PW121           ENGINE                                                                     PWA   PW121 PW121       52124NE                                              MAKING METAL    W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN)  METAL CONTAMINATION OF TURBOMACHINE OIL SYSTEMS DETECTED VIA TREND MONITORING ANALYSIS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         4  T          E20NE                
20061205000242006120500024EA  2006       12         5          CA061123003      220061123G7230                IMPELLER                                                                   PWA   PT6   PT6A50      52043EA                              ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) "IMPACT DAMAGE AND A CRACKED IMPELLER". A CRACK IN THE OUTER IMPELLER WAS FOUND.   (TC# 20061123003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             4  T          E4EA                 
20080306002782008030600278EA  2008       3          6          CA061123005      220061121G7322055211313       FLAPPER VALVE   CESSNA                  CESSNA172   172N        2072434CE  LYC   O320  O320H2AD    41508EA  MCAULY1C160 1C160DTM    GL  CARB HEAT BOX   WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       705  705                                                       (CAN) DURING PROGRESSIVE CARE OPERATION NR 2, INSP OF THE CARBURETOR HEAT BOX (P/N 05521644) REVEALED THAT THE 2 ALUMINUM RIVETS THAT HOLD THE FLAPPER DOOR TO THE ACTUATOR SHAFT WERE VERY CLOSE TO SHEARING OFF. IF THE ALUMINUM RIVETS DID SHEAR, AND THE AC WAS FLYING IN CARBURETOR ICING CONDITIONS, ENGINE FAILURE COULD OCCUR. THERE IS ALSO THE CONCERN OF PIECES OF RIVETS BEING INGESTED INTO THE ENGINE. THE CARB AIR BOX WAS PURCHASED NEW FROM MFG, INSTALLED 16 MONTHS AGO AND IN SERVICE ON THIS ENGINE FOR 704.7 HRS. NOT SO LONG AGO, MFG USED STEEL RIVETS INSTEAD OF ALUMINUM. THIS DID NOT SEEM TO BE A PROBLEM IN THE PAST WITH STEEL RIVETS. (TC NR 20061123005)                                                         1H71 3O3  ONT3A12    E274    5  NP910     
20070820000282007082000028CE  2007       8          20         CA061123006      120061120G5420085150047       CAP                                     CESSNA414   414         2075908CE  CONT  O520  TSIO520N    17040SO  MCAULY3AF32C3AF32C505   GL  LT NACELLE      CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) CRACK NOTED AT LT NACELLE CANTED BULKHEAD CAP.  CAP REPAIRED. (TC NR 20061123006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1L72 3O3  ORTA7CE    E8CE    5  CP22EA    
20061205000272006120500027EA  2006       12         5          CA061123008      120061122G5610NP13932112      WINDSHIELD                              CNDAIRCL600 CL6002C10   1390015EA                                                               COCKPIT         CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA       7288                                                           (CAN) RH WINDSHIELD CRACK WHILE IN CRUISE. (TC# 20061123008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F    RTA21EA                        
20061205000252006120500025EA  2006       12         5          CA061124001      220061123G7230                COMPRESSOR                                                                 PWA   PT6   PT6A34      52043EA                              ENGINE          DAMAGED         W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) ENGINE TEARDOWN RELATED TO AN IFSD AND A POSSIBLE COMPRESSOR FAILURE.  TEARDOWN NOT YET CONCLUSIVE. IT WAS NOT A COMPRESSOR FAILURE BUT APPEARS TO BE FAILURE OF ONE OR MORE CT BLADES AND THEN CAUSED A STRUCTURAL FAILURE OF THE GAS GENERATOR CASE, WHICH THEN RESULTED IN COMPRESSOR DAMAGE.  COMPRESSOR ROTOR WAS LOCKED UP BUT THE PT ROTOR WAS FREE TO ROTOATE. IT APPEARS TO BE UNECONOMICAL TO REPAIR THIS ENGINE. (TC# 20061124001)                                                                                                                                                                                                                                                                                                    4  T          E4EA                 
20061205000262006120500026EU  2006       12         5          CA061124002      320061123G6197697070212       BUSS BAR                    R408        BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R4304 R4304*      EU  NR 1 PROP       SHORTED         W      E   ENGINE SHUTDOWN                                                                                 F  FLT CONT AFFECTED                                                             CRCRUISE         1                      CA            10    NA                                                  (CAN) NO.1 ENGINE SHUTDOWN DURING FLIGHT DUE PEC FAIL CAUTION LIGHT AND PROP SPEED AT 1060 RPM. FAULT CODES LH CH A/B 160 AND 162. MAYDAY CALLED AND A NORMAL LANDING PERFORMED. PAX DEBRIEFED DURING TAXING AND AFTER PARKING. MAINTENANCE DISPATCHED TO TROUBLE SHOOT. NOTE PROP ASSY ONLY INSTALLED LAST WEEK. TECHNICIAN FOUND PROP HEATER BUSBAR ASSEMBLY CHAFED BY NO.1 PROP MPU BRACKET. BUSBAR REPLACED AND BUSBAR/PICK-UP CLEARANCE CHECKED OK. ENGINE RUN, PROP RPM AND PROP DE-ICE CHECKED OK. (TC# 20061124002)                                                                                                                                                                                                                     2H72 4T4  TRTA13NM   E00062EN6  CP890     
20070820000292007082000029EA  2007       8          20         CA061124003      120061123G2750                FLAP SYSTEM                             CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              TE FLAPS        MALFUNCTIONED   W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA       1115111151                                                     (CAN) DURING APPROACH UPON INITIAL FLAP DOWN SELECTION, FLAP FAILED TO MOVE AND CREW RECEIVED (FLAP FAIL) MESSAGE ON EIACS. APPROACH CONTINUED AND NORMAL FLAPLESS LANDING CARRIED OUT. MAINTENANCE INSPECTION CARRIED OUT, NO EVIDENCE OF TWISTING, SKEWING OR DEFORMATIONS NOTED. FECU (FLAP ELECTRONIC CONTROL UNIT) CIRCUIT BREAKERS CYCLED IAW RE-SET PROCEDURE AND FLAPS FUNCTION CHECKED NORMAL OPERATIONS. (TC NR 20061124003)                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA21EA   E15NE                
20070820000302007082000030SW  2007       8          20         CA061124005      120061121G57532736041001      CHANNEL                                 SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP                              TE FLAP         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       19186                                                          (CAN) DURING OVERHAUL OF THE RT FLAP ASSY, THE CENTER HINGE CHANNEL WAS REMOVED FOR REPLACEMENT AND WAS FOUND CRACKED BETWEEN (2) RIVET HOLES. THE CHANNEL HAS BEEN REPLACED.   (TC NR 20061124005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4T4  TRTA8SW    E4WE                 
20061205000202006120500020CE  2006       12         5          CA061124006      120061124G3060                BOOT            MCAULY      B3D36C432   CESSNA206   T206H       2073303CE  LYC   O540  TIO540AJ1A       EA  MCAULY3D36C B3D36C432   GL  PROPELLER DE-ICEFAILED          W      K   NONE                                                                                            J  WARNING INDICATION                                                            ININSP/MAINT     1                      CA       294        030476                                              (CAN) DURING PHASE NR 2 INSPECTION IT WAS NOTED ON PRE-INSPECTION RUNUP THAT THE PROP DE-ICE WAS INOPERATIVE. INVESTIGATION REVEALED THAT 2 OF THE 3 DE-ICE BOOT LEADS WERE DEFECTIVE. NEW PARTS ORDERED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3O3  ORTA4CE    E14EA   5  CP58GL    
20070131001022007013100102SW  2007       1          31         CA061124007      120061124G5531410009505       SPAR CAP                                GULSTM690TP 690         0141720SW  GARRTTTPE331TPE3315251K      NM  HARTZLHCB3T HCB3TN5     GL  VERTICAL STAB   CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) CRACK FOUND IN LT HAND SPAR CAP 1.5 IN. FROM BOTTOM. (TC NR 20061124007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H72 3T4  T  2A4     E2WE    6  CP15EA    
20070820000312007082000031CE  2007       8          20         CA061124008      120061124G32100541121497      SUPPORT                                 CESSNA172   172K        2072430CE  LYC   O320  O320E2D     41508EA  MCAULY1A175 1A175ATM    GL  MLG             CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       18284                                                          (CAN) AIRCRAFT BEING SERVICED FOR MFG CARE NR 4 (200-HOUR) INSPECTION AND CHANGED OVER TO SKIS.  LT OB SUPPORT FOR LANDING GEAR WAS FOUND TO HAVE SEVERAL CRACKS.  PART WAS REPLACED WITH NEW.   AIRCRAFT IS OPERATED AS FLOATPLANE AND SKIPLANE FOR FLIGHT TRAINING. (TC NR 20061124008)                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3O3  ONT3A12    E274    5  NP857     
20061205000292006120500029NM  2006       12         5          CA061124009      120061121G561058935734        WINDOW                                  BOEING737   737*               NM  CFMINTCFM567CFM567B22   13802NE                              COCKPIT         DELAMINATED     W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       13516                                                          (CAN) ON NOV. 22, 2006 A/C 208 DURING INSPECTION OF THE NR 5 RT EYEBROW WINDOW IT WAS NOTED THAT THE NR 4 RT EYEBROW WINDOW WAS DELAMINATED BEYOND LIMITS. THE AIRCRAFT WAS REMOVED FROM SERVICE AND THE NR 4 RT EYEBROW WINDOW WAS REPLACED. BOEING IS AWARE OF THIS IN SERVICE ISSUE AND HAS INITIATED SERVICE RELATED PROBLEM (SRP) 56-0018. BOEING HAS ALSO ISSUED SERVICE BULLETIN 737-56-1017 TO PROVIDE 737NG OPERATORS WITH AN OPTION TO REPLACE THE NR 4 AND 5 WINDOWS WITH STRUCTURAL PLUGS. WESTJET IS PLANNING ON INCORPORATING THIS SERVICE BULLETIN.                                                                                                                                                                              2L72 4F4  FRTA16WE   E00055EN             
20070125001472007012500147SW  2007       1          25         CA061124010      120061120G6320204040353023    CASE            BELL                    BELL  205   205A1       1181414SW                                                               TRANSMISSION    CRACKED         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       109661520  ABT364                                              (CAN) CRACKING AT INPUT QUILL BOSS OF MAIN ROTOR TRANSMISSION. (TC NR 20061124010)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1G71 4U      H1SW                         
20070125001482007012500148SW  2007       1          25         CA061124011      120061114G781023008052        COLLECTOR                               BELL  206   206L1       1182107SW  ALLSN 250C  250C28B     03013GL                              ENGINE EXHAUST  CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            1278                          CAT28028                    (CAN) DURING ENGINE MAINTENANCE, THE HORIZONTAL FIRESHIELD WAS REMOVED AND (2) CRACKS WERE NOTED AT THE 5 O`CLOCK AND 7 O`CLOCK POSTION IN THE EXHAUST COLLECTOR.   TURBINE REMOVED REPAIRED RE-INSTALLED. (TC NR 20061124011)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1G71 3U3  U  H2SW    E1GL                 
20070125001502007012500150CE  2007       1          25         CA061127001      120061123G3230MC815AS1        CONTROLLER                              BEECH 100   A100        1152915CE  PWA   PT6   PT6A28           EA  MCAULY4HFR344HFR34C762  NE  MLG             UNSERVICEABLE   W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) FLIGHT CREW REPORTED LANDING GEAR WOULD NOT RETRACT AFTER TAKE-OFF. AFTER TROUBLESHOOTING THE MOTOR CONTROLLER WAS FOUND UNSERVICEABLE.  MOTOR CONTROLLER WAS REPLACED, GEAR SWINGS COMPLETED AND THE AIRCRAFT RETURNED TO SERVICE. THIS UNIT HAD 928 LANDINGS SINCE OVERHAUL; INSPECTION REQUIREMENTS ARE 8000 LANDING OVERHAUL AND 1000 LANDING POINT CHECK.                                                                                                                                                                                                                                                                                                                                                                            1L72 3T4  T  A14CE   E4EA    6  C3PNE     
20070125001522007012500152CE  2007       1          25         CA061127002      120061126G3260                UNKNOWN                                 BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE  HARTZLHCE4A HCE4A3I     NE  MLG             UNKNOWN         W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      CA                                                                      (CAN) AIRCRAFT DEPARTED, DURING CLIMB THE LANDING GEAR RED UNSAFE LIGHT ILLUMINATED. GEAR WAS CYCLED AND LIGHT WOULD NOT EXTINGUISH. GEAR WAS SELECTED DOWN AND (3) GREEN ILLUMINATED WITH NO RED HANDLE. CREW ELECTED TO RETURN TO MAINTENANCE.  MAINTENANCE INSPECTED AND SWUNG GEAR WITHOUT FAULT.  AIRCRAFT OPERATING WITHOUT FURTHER INSTANCE. WEATHER EXTREMELY COLD ON DAY OF OCCURRENCE. (TC NR 20061127002)                                                                                                                                                                                                                                                                                                                            2L72 4T4  TRTA24CE   E26NE   5  CP10NE    
20061205000212006120500021EA  2006       12         5          CA061127003      120061123G5712600102211       RIB                                     CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              LT WING         CHAFED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) IN LEFT HAND WING TANK INBOARD BAY, STEAL BRAIDED FUEL LINE PART NUMBER 00624-AE7013343N0220 WAS FOUND CHAFING ON THE WING RIB STIFFENER PART NUMBER 600-10221-1. CHAFING OCCURRED APPROXIMATELY 9 1/2 INCHES FROM BOTTOM OF TANK. DAMAGE EXTENDS OVER AN AREA OF APPROXIMATELY 3/4 OF AN INCH WITH THE MAIN DAMAGE COVERING APPROXIMATELY 5/8 OF AN INCH INSIDE THE 3/4 INCH AREA. SEE ATTACHED PHOTOS. DAMAGE IS TAPERED FROM 0 INCHES TO APPROXIMATELY 0.120 INCHES AREA HAS NOT YET BEEN DRESSED SO FINAL DEPTH MEASUREMENTS ARE NOT AVAILABLE.   (TC# 20061127003)                                                                                                                                                                   2L72 4F4  FRTA21EA   E15NE                
20080201000982008020100098SW  2008       2          1          CA061128001      120061124G2810206063688001    LINE                                    BELL  206   206L        1181522SW  ALLSN 25OC  250C20R          GL                              FUEL SYSTEM     LEAKING         W      O   OTHER                                                                                           KB FLUID LOSS                SMOKE/FUMES/ODORS/SPARKS                            NRNOT REPORTED   1                      CA                                                                      (CAN) DURING A SCHEDULED FLIGHT, FUEL FUMES WERE DETECTED IN REAR CABIN AREA. A/C RETURNED TO BASE WITH NO PROBLEMS NOTED. A/C INSPECTED AND FWD FUEL TANK VENT LINE FOUND WEEPING WHEN REAR TANK WAS FILLED TO CAPACITY. LINE REMOVED AND REPLACED. LINE INPECTED AND FOUND TO BE ORIGINAL FROM DATE OF A/C MFG 1975. RECOMMEND REPLACEMENT DATE OF FLEX HOSE BE ADDED TO MM. (TC NR 20061128001)                                                                                                                                                                                                                                                                                                                                              1G71 3U3  U  H2SW    E4CE                 
20061205000222006120500022    2006       12         5          CA061128002      420061123G3421ASN43           INDICATOR                               BRAERO748   HS7482A     4231001EU  RROYCEDART  DART5342         EU                              NR 1 HORIZON    FAILED          W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA            1459                                                      (CAN) DURING DEPARTURE THE CAPTAINS HORIZON FAILED ON CLIMB OUT. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WITHOUT FURTHER PROBLEM. MAINTENANACE REPLACED THE NO1. GYRO AND THE AIRCARFT WAS RETURNED TO SERVICE. (TC# 20061128002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 3T4  T  A24EU   A196                 
20070125001532007012500153CE  2007       1          25         CA061128003      120061116G571220062           RIB                                     CESSNA340   340A        2076405CE  CONT  O520  TSIO520NB   17040SO  MCAULY3AF34C3AF34C*     GL  RT WING         WRONG PART      W      O   OTHER                                                                                           W  INADEQUATE Q C                                                                NRNOT REPORTED   1                      CA       1324                                                           (CAN) DURING A ROUTINE INSPECTION DISCOVERED LT AND RT WING RIBS AT STATION 117.48 TO BE CONFLICTING WITH THE FLAP RIB AT SIMILAR LOCATION WHEN FLAPS ARE RETRACTED.  AFTER INSPECTION FOUND THAT THE SPOILER DOUBLER INSTALLED IN 1995 WAS THE WRONG DIMENSION ALLOWING WING RIB TO BE POSITIONED INCORRECTLY.  UPON FARTHER INVESTIGATION FOUND THE TEMPLATE NR 8005T AND THE INSTALLATION INSTRUCTIONS NR SP8000 SUPPLIED WITH THE STC SA4948NM TO BE CONTRADICTING EACH OTHER IN RESPECT TO THE NEW LOCATION OF THE WING RIB. THIS COULD BE VERY SERIOUS, IF ONE OF THE FLAPS BECAME INOPERATIVE DUE TO THE FACT THAT THE RIBS HOOKED ON EACH OTHER. (TC NR 20061128003)                                                                    1L72 3O3  O  3A25    E8CE    5  CP22EA    
20080219001022008021900102SW  2008       2          19         CA061128004      120061117G5320206031202015    SUPPORT         BELL        206031200   BELL  206   206B        1181511SW  ALLSN 250C  250C20      03013GL                              FUSELAGE        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       14060                                                          (CAN) STRAP PN 206-031-200-076 WAS FOUND CRACKED AT INSPECTION.  WHEN IT WAS REMOVED, SUPPORT PN 206-031-202-015 WAS ALSO FOUND CRACKED. BOTH WERE REPLACED IAW MFG INSTRUCTIONS. (TC NR 20061128004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1G71 3U3  U  H2SW    E4CE                 
20061205000592006120500059EA  2006       12         5          CA061128005      220061115G7230                COMPRESSOR                              DHAV  DHC6  DHC6100     2802610EA  PWA   PT6   PT6A20      52043EA                              NR 2 ENGINE     DAMAGED         W      C   ABORTED TAKEOFF                                                                                 YJ ENGINE STOPPAGE           WARNING INDICATION                                  TOTAKEOFF        1                      CA       120997187                                                      (CAN) ON POWER APPLICATION FOR TAKEOFF, THE #2 ENGINE ACCELERATED NORMALLY TO TAKEOFF POWER.  AS THE AIRCRAFT BEGAN TO CLIMB ONTO THE STEP, THE F/O OBSERVED A FLASH OF LIGHT AND HEARD A BANG FROM THE ENGINE.  THE TAKEOFF WAS REFECTED AND THE AIRCRAFT RETURNED TO THE DOCK.  THE ENGINE WAS REPLACED AND THE AIRCRAFT WAS RETURNED TO SERVICE.  INVESTIGATION REVEALED THAT THE COMPRESSOR SECTION OF THE ENGINE HAD FAILED.  RESULTS OF THE TEARDOWN WILL BE FORTHCOMING.  THIS ENGINE HAS BEEN OPERATING "ON CONDITION"  SINCE PURCHASE IN 2002. (TC# 20061128005)                                                                                                                                                                       1H72 3T3  TRTA9EA    E4EA                 
20080219001142008021900114CE  2008       2          19         CA061128008      120061120G243240576           BATTERY                                 BEECH 200   B200        1152922CE  PWA   PT6   PT642A           NE  HARTZLHCB3T HCB3TN3     GL  MAIN            THERMAL RUNAWAY W      H   DEACTIVATE SYST/CIRCUITS                                                                        MB OVER TEMP                 SMOKE/FUMES/ODORS/SPARKS                            ININSP/MAINT     1                      CA       3112 55                                                        (CAN) WHILE CONNECTED TO A GPU, DURING ROUTINE MAINTENANCE, THE TECHNICIANS NOTED SMOKE IN THE AREA OF THE BATTERY BOX COMPARTMENT. THE GPU WAS IMMEDIATELY DISCONNECTED, BATTERY POWER TURNED OFF AND THE BATTERY DISCONNECTED FROM THE AIRCRAFT BY REMOVAL OF THE ALCON CONNECTOR AT THE BATTERY. THE BATTERY HAD OVERHEATED AND WENT INTO A THERMAL RUNAWAY CONDITION. THE BATTERY WAS REPLACED AS WELL AND THE BATTERY CHARGE MONITORING PRINTED CIRCUIT CARD. (TC NR 20061128008)                                                                                                                                                                                                                                                          1L72 4T4  T  A24CE   E4EA    6  CP15EA    
20080219001202008021900120EA  2008       2          19         CA061129003      120061124G2710N025            MASTER LINK                             FOUND FBA   FBA2C       3640102EA                                                               AILERON CONTROL DEFECTIVE       W      A   UNSCHED LANDING                                                                                 F  FLT CONT AFFECTED                                                             CRCRUISE         1                      CA       31                                                             (CAN) DURING FIGHT ID 2C3-30 THE MASTER LINK (N025) FELL OFF THE COPILOTS AILERON CHAIN CAUSING A LOSS OF AILERON CONTROL FROM THE COPILOTS SIDE. THE FLIGHT TEST ENGINEER WAS ABLE TO COLLECT ALL THE PIECES FROM THE MASTER LINK DURING THE FLIGHT HOLD AND THE CHAIN FROM JAMMING THE AILERON CONTROL FOR THE REST OF THE FLIGHT. THE PILOT WAS ABLE TO FLY AND LAND THE AC SAFELY WITHOUT USING THE AILERONS. THE AC IS AN EXPERIMENTAL AC IN A FLIGHT TEST PROGRAM, THIS MODEL USES THE SAME AILERON CONTROL SYS AS THE 2C1 AND 2C2 MODELS. BEING THE MFG WE HAVE INITIATED A MATERIAL REVIEW AND WILL BE ISSUING A SB.  (TC NR 20061129003)                                                                                             1H71 3O      A7EA                         
20061205000042006120500004    2006       12         5          CA061129004      420061129G2210                CLAMP                                   DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A27      52043EA                              BRIDLE CABLE    DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) THIS DEFECT WAS ORIGINALLY IDENTIFIED IN THE SUBJECT AIRCRAFT FLIGHT LOG DATED OCTOBER 26, 2006.SUBSEQUENT INVESTIGATION BY OUR QUALITY ASSURANCE DEPARTMENT GENERATED THE REQUEST THAT A SDR BE FILED. THE AIRCRAFT ARRIVED IN OTTAWA FOR A SCHEDULED INSPECTION WITH A REPORTED AUTO-PILOT SNAG. " AUTO-PILOT U/S - SOMETIMES WON`T ENGAGE, WHEN IT DOES - IT YAWS & BANKS". ON SUBSEQUENT GROUND TESTING THE "BRIDAL CABLES" TO THE RUDDER SERVO-MOTOR WERE FOUND TO BE COMPLETELY WITHOUT TENSION. THE INSTALLATION WAS INSPECTED AND IT WAS DETERMINED THAT EVEN THOUGH THE BRIDLE CABLE TO RUDDER CABLE CLAMPS WERE INSTALLED AND TORQUED CORRECTLY THE WITNESS MARKS WERE NOT VISIBLE. IT IS BELIEVED THAT THE CLAMP SLIPPED ON THE1H72 3T4  TRTA9EA    E4EA                 
20070125001542007012500154CE  2007       1          25         CA061129005      120061129G2820050011849       LINE                                    CESSNA172   172S        2072439CE  LYC   IO360 IO360L2A         EA  MCAULY1A170 1A170*      GL  FUEL RETURN     WORN            W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       2810                                                           (CAN) A FUEL LEAK WAS NOTED ON THE AIRCRAFT.  UPON INSPECTION THE FUEL LINE BETWEEN THE FCU AND FUEL RESERVOIR WAS FOUND WORN.  THE NOSE WHEEL STEERING ROD HAD BEEN RUBBING INTO THE LINE, AND WORN A GROOVE DEEP ENOUGH TO ALLOW FUEL TO LEAK.  THE FUEL LINE IS ALUMINIUM, AND THE STEERING ROD IS STEEL.  NO DAMAGE WAS NOTED ON THE STEERING ROD.  (2) OF THESE TYPE OF AIRCRAFT ARE OPERATED, AND THE SECOND WILL BE INSPECTED FOR THE SAME TYPE OF PROBLEM. (TC NR 20061129005)                                                                                                                                                                                                                                                          1H71 3O3  ONT3A12    1E10    5  NP857     
20061205000052006120500005EA  2006       12         5          CA061129006      120061129G3220AW24VDU         BEARING                                 CNDAIRCL215 CL2151A10   1900320EA                                                               LT MLG          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) LT FOLDING STRUT LOWER BEARING CRACKED AT 4 PLACES.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2H72 4R    RTA14EA                        
20061205000192006120500019NM  2006       12         5          CA061130001      120061124G27403994001013      ACTUATOR                                BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA                              PITCH TRIM      FAILED          W      A   UNSCHED LANDING                                                                                 F  FLT CONT AFFECTED                                                             CLCLIMB          1                      CA                                                                      (CAN) PITCH TRIM CAUTION LIGHT AND AUTO TRIM FAIL MESSAGE APPEARED DURING CLIMB.  AIRCRAFT RETURNED TO BASE. WIRING CHECKS CARRIED OUT BETWEEN THE FCECU AND PITCH TRIM ACTUATOR. (FCECU CODES 67, 63, E7 AND E3) ACTUATOR REPLACED. (TC# 20061130001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2H72 4T4  TRTA13NM   E00062EN             
20061205000702006120500070CE  2006       12         5          CA061130002      120061109G5740122005311       ATTACH BRACKET                          CESSNA206   U206F       2073333CE  CONT  O520  IO520F      17032SO                              AILERON         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       8544                                                           (CAN) AILERON ATTACH BRACKET CRACKED ON RADIUS LWR LT INBD FWD. PART REMOVED AND REPLACED WITH NEW P/N 1220053-17, ALL OTHER BRACKETS CHECKED NO CRACKS FOUND.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H71 3O3  O  A4CE    E5CE                 
20061212000972006121200097EU  2006       12         12         CA061130003      120061001G261351533172        ELEMENT                                 SAAB  SF340 SF340A      7850100EU  GE    CT7TP CT75A2      30030NE  ROTOL R389  R3894123F26 NE  OVERTEMP        CHAFED          W      E   ENGINE SHUTDOWN                                                                                 N  FALSE WARNING                                                                 CLCLIMB          1                      CA       45559                                                          (CAN) AIRCRAFT RETURNED TO BASE SHORTLY AFTER DEPARTURE DUE TO A NR 2 BLEED AIR LEAK LIGHT ILLUMINATION DURING CLIMB OUT. THE BLEED AIR WAS SELECTED OFF BUT THE LIGHT REMAINED ILLUMINATED. IAW THE REQUIRED PROCEDURES THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT LANDED UNEVENTFUL. INSPECTION OF THE AIRCRAFT BY MAINTENANCE DETERMINED THAT THE WARNING LIGHT WAS A FALSE INDICATION CAUSED BY A CHAFED BLEED AIR SENSE LINE IN THE AFT RT WING TRAILING EDGE. THE AFFECTED SENSE LINE WAS REPLACED. AN ADDITIONAL INSPECTION OF THIS AREA HAS BEEN ISSUED FOR COMPLETION ON THE ADJACENT SIDE OF THIS AIRCRAFT AS WELL AS A PLANNING CARD TO INSPECT THE SECOND AIRCRAFT IN THE FLEET.     (TC NR 20061130003)                              2L72 4T4  TRTA52EU   E8NE6   6  CP30NE    
20070125001552007012500155EA  2007       1          25         CA061130004      120061128G3234                RELEASE CABLE                           CNDAIRCL600 CL6002B19   1900309EA                                                               MLG LEVER       DISLODGED       W      K   NONE                                                                                            L  NO TEST                                                                       ININSP/MAINT     1                      CA                                                                      (CAN) DURING OF OPERATIONAL TEST OF THE LANDING GEAR MANUAL RELEASE SYSTEM THE NLG HAS NOT BEEN EXTENDED.AFTER INVESTIGATION FOUND THAT NLG RELEASE CABLE IS OUT OF PULLEY INSTALLED INSIDE OF THE LEVER P/N 600-85015-29. SEVERAL DAYS LATER INSPECTING ANOTHER AIRCRAFT.  A SIMILAR SNAG HAS BEEN DETECTED. BOTH CABLES WERE REINSTALLED AND ADJUSTED IAW AMM,OPERATIONAL TEST CARRIED OUT AND FOUND SERVICEABLE. SEE ATTACHMENTS: LEVER AFFECTED IS ITEM NR 225 AND PULLEY IS ITEM NR 155.                                                                                                                                                                                                                                                   2L72 4F    RTA21EA                        
20070126003462007012600346NM  2007       1          26         CA061130005      120061126G4920APS2000         APU                                     BOEING737   737522      138449FNM  CFMINTCFM56 CFM563C     13802EU                              APU BAY         DAMAGED         W      K   NONE                                                                                            J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      CA       1947782                                                        (CAN) MFG WAS GETTING READY TO DEPART. ON ATTEMPTING TO START THE APU, THE FAULT LIGHT CAME ON AND THE APU FAILED TO START.  THE ITEM WAS DEFERRED TO (MEL) MINIMUM EQUIPMENT LIST AND THE FLIGHT CONTINUED TO ITS DESTINATION.  ON INVESTIGATION THERE WAS CONSIDERABLE DAMAGE TO THE GEARBOX AND STARTER SHAFT.  THIS UNIT WAS REMOVED FOR A SIMILAR PROBLEM 82 HOURS PREVIOUSLY AND HAD BEEN OVERHAULED.  ONCE A TEARDOWN REPORT IS RECEIVED, A FOLLOW UP WILL BE SUBMITTED. (TC NR 20061130005)                                                                                                                                                                                                                                             2L72 4F4  FRTA16WE   E21EU                
20061205000162006120500016EA  2006       12         5          CA061130006      120061128G29136619003         PUMP                                    CNDAIRCL600 CL600*             EA                                                               HYDRAULIC SYS   LEAKING         W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA       3569                                                           (CAN) DURING CRUISE, THE NR 1 HYDRAULIC SYSTEM WAS DEPLETING AND WAS DOWN TO 20% OF CAPACITY. NO ASSOCIATED EICAS MESSAGE. AIRCRAFT WAS DIVERTED TO MAINTENANCE BASE.LEAK WAS FOUND AT NR 1 HYDRAULIC PUMP. PUMP WAS REPLACED. AIRCRAFT GROUND RUNS CARRIED OUT, SYSTEM REPLENISHED AND AIRCRAFT RETURNED TO SERVICE.                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F    RTA21EA                        
20061205000022006120500002EA  2006       12         5          CA061201001      120061201G271021592315122     CONTROL CABLE                           CNDAIRCL215 CL2151A10   1900320EA                                                               AILERONS        WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       151                                                            (CAN) LT AILERON CONTROL CABLE WORNED IN FAIRLEAD, ACCESS  PANEL 740-2 (RT SIDE). CABLE NEEDS REPLACEMENT. THIS CABLE HAS BEEN REPLACED ON 2005-11-22 AND CUMULATED 151 HOURS FLYING TIME.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2H72 4R    RTA14EA                        
20080219001222008021900122EA  2008       2          19         CA061201002      120061129G554133700K5         SPAR            SCWZER      33700K3     SCWZERSG2   SGS233A     8051606EA                                                               RUDDER          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3891                                                           (CAN) DURING THE COMPANY 12 YEAR STRUCTURAL INSPECTION AND REPAIR PROGRAM (SIRP), A CRACK WAS FOUND IN ON RUDDER SPAR ON THE OUTER LT EDGE OF THE UPPER HINGE ATTACH POINT. LPI INSPECTION WAS USED TO VERIFY THE CRACK (TC NR 20061201002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1K00         G2EA                         
20080219001252008021900125EA  2008       2          19         CA061201003      120061129G554133700K5         SPAR            SCWZER      33700K3     SCWZERSG2   SGS233A     8051606EA                                                               RUDDER          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       4138                                                           (CAN) DURING THE COMPANY 12 YEAR STRUCTURAL INSPECTION AND REPAIR PROGRAM (SIRP), A CRACK WAS FOUND ON THE RUDDER SPAR ON THE OUTER LT EDGE OF THE UPPER HINGE ATTACH POINT. (TC NR 20061201003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1K00         G2EA                         
20080219001282008021900128SW  2008       2          19         CA061201004      120061124G2810714931L         TANK                                    BBAVIA8     8GCBC       1220803SW  LYC   O360  O360C2E     41514EA  MCAULY1A200 1A200*      GL  WING            CRACKED         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       2504                                                           (CAN) AIRCRAFT HAD RETURNED TO MAINTENANCE FACILITY FOR WINTER STORAGE. FUEL STAINS WERE NOTICED ON THE BOTTOM OF THE WING NEAR THE TRAILING EDGE. LT IB TANK WAS REMOVED AND A 1.5 INCH CRACKED WAS FOUND ON THE RADIUS OF THE LATERAL RE-ENFORCEMENT INDENT OF TANK. (TC NR20061201004)                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3O3  O  A21CE   E286    5  NP874     
20070126003492007012600349EA  2007       1          26         CA061201006      120061104G2750                FLAP SYSTEM                             CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              WING            MALFUNCTIONED   W      K   NONE                                                                                            F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA       4750 4750                                                      (CAN) DURING APPROACH WHEN FLAPS SELECTED TO 45 DEG , FLAPS REMAINED AT 30DEG AND (FLAP FAIL) MESSAGE ON EICAS, CONTINUED APPROACH AND NORMAL LANDING WITH FLAPS AT 30 DEG EXTENSION.  MAINTENANCE CLEANED AND LUBRICATED FLAP DRIVE SHAFTS, FLAP ACTUATORS GREASED/PURGED. NO WATER INDICATIONS NOTED. FLAPS CYCLED NUMEROUS TIMES, NORMAL OPERATION AIRCRAFT RETURNED TO SERVICE. (TC NR 20061201006)                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRTA21EA   E15NE                
20070126003542007012600354EA  2007       1          26         CA061201007      120061101G2750                FLAP SYSTEM                             CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              WING            MALFUNCTIONED   W      K   NONE                                                                                            F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA       4760 4760                                                      (CAN) DURING APPROACH FLAPS 20DEG SELECTED AND FLAPS AT 20DEG, WHEN 30DEG SELECTED FLAPS REMAINED AT 20DEG. NORMAL LANDING WITH FLAPS AT 20DEG. MAINTENANCE UNABLE TO DUPLICATE FAULT ON GROUND. AIRCRAFT FERRIED TO MAINTENANCE BASE. MAINTENANCE CARRIED OUT TORQUE CHECK OF FLAP DRIVE, NO FAULTS FOUND. OPERATIONAL TEST OF FLAPS CARRIED OUT WITH NO FAULTS FOUND. (TC NR 20061201007)                                                                                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA21EA   E15NE                
20061205000182006120500018NM  2006       12         5          CA061204001      120061128G5610NP15790213      WINDOW                                  DHAV  DHC8  DHC8*              NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  COCKPIT         FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA       32287                                                          (CAN) DURING CRUISE, THE PILOT`S SIDE WINDOW OUTER PANE SHATTERED. AN UNEVENTFUL LANDING WAS CONDUCTED. ENGINEERING INSPECTED THE AIRCRAFT AFTER LANDING AND FOUND THE SIDE WINDOW OUTER PANE HAD SHATTERED.  THE SIDE WINDOW ASSEMBLY WAS REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC# 20061204001)                                                                                                                                                                                                                                                                                                                                                                                                                                     2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20061205000032006120500003EA  2006       12         5          CA061204002      120061130G3320336710          BALLAST                                 DHAV  DHC3  DHC3        2800202EA                                                               CABIN LIGHTS    FAILED          W      K   NONE                                                                                            H  ELECT. POWER LOSS-50 PC                                                       ININSP/MAINT     1                      CA       91                                                             (CAN) ON POWER UP OF AIRCRAFT, CABIN LIGHT BALLASTS FAIL. THIS AIRCRAFT HAS HAD 10 BALLAST UNITS 3367-10 REPLACED. (TC# 20061204002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H71 3R      A815                         
20070126003572007012600357WP  2007       1          26         CA061204003      220061204G7200TPE33112UHR     ENGINE                                  FRCHLDSA227 SA227DC     3377521SW  GARRTTTPE331TPE33112UHR      WP  MCAULY4HFR344HFR34C652  NE                  MAKING METAL    W      K   NONE                                                                                            J  WARNING INDICATION                                                            ININSP/MAINT     1                      CA                                                                      (CAN) DURING ENGINE MAINTENANCE, IT WAS NOTICED THAT THE ENGINE OIL FILTER BYPASS PIN HAD POPPED. THE OIL FILTER WAS REMOVED AND INSPECTED. METAL CONTAMINATION WAS FOUND AND A SOAP SAMPLE WAS TAKEN. (TC NR 20061204003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4T4  TRTA18SW   E4WE    6  C3PNE     
20070126003602007012600360EU  2007       1          26         CA061204004      120061128G21619599020135      CONTROL VALVE                           PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  CABIN TEMP      MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA       1309413094                                                     (CAN) AIRCRAFT WAS ON CLIMBOUT GOING THROUGH 6000 FEET WHEN ECS LIGHT CAME ON AND CABIN STARTED TO DE-PRESSURIZE. AIRCRAFT RETURNED TO RANKIN INLET WHERE MAINTENANCE DISCOVERED THAT TCA VALVE WAS STUCK IN THE FULL OPEN POSITION AND EXCESS HEAT TRIPPED THE SYSTEM OFF. TCA VALVE WAS REPLACED AND ECS SYSTEM CHECKED OK. (TC NR 20061204004)                                                                                                                                                                                                                                                                                                                                                                                               1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20070126003642007012600364EA  2007       1          26         CA061204005      120061201G3244362K821         TIRE                                    CNDAIRCL600 CL600*             EA                                                               NR 3            SEPARATED       W      O   OTHER                                                                                           O  OTHER                                                                         LDLANDING        1                      CA                                                                      (CAN) NR 3 TIRE HAS THROWN A TREAD. CREW INSPECTED FLAP/ GEAR FOR DAMAGE, NO DAMAGE FOUND JUST RUBBER TRANSFER.   SUSPECT IT HAPPENED ON ARRIVAL LAST NIGHT. BUT NOT DISCOVERED UNTIL IN THE AM. (TC NR 20061204005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F    RTA21EA                        
20070126003702007012600370NE  2007       1          26         CA061204006      220061204G7230                BLADES                                                                     PWA   PT6   PT6A114A    52043NE                              ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       8000 4100                                                      (CAN) SEE REPORT ATTACHED  CRACK INDICATIONS WERE FOUND ON THE CT BLADES AT OVERHAUL. CRACKS WERE FATIGUE RELATED ON ALL THE CT BLADES. HOWEVER, THE ATTACHED REPORT STATES THAT THE CT BLADES DID NOT FAIL IN CREEP AS DETAILED IN MFG SILS, DUE TO OVERTEMP OR EXCEEDING ENGINE LIMITATIONS. FAILURE APPEARS TO BE DUE TO FLAP MODE VIBRATIONS.  PLEASE REFER TO ATTACHED ENGINEERING REPORT FOR DETAILS. (TC NR 20061204006)                                                                                                                                                                                                                                                                                                                        3  T          E4EA                 
20070129001422007012900142NM  2007       1          29         CA061204007      120061201G2910MS219134        O-RING          PARKERHANFIN9451693     DHAV  DHC8  DHC8*              NM                                                               HYDRAULIC SYS   FAILED          W      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  APAPPROACH       1                      CA       16   16    0841                                                (CAN) WHILE ON APPROACH AT 10,000 FEET CREW NOTICED NR 2 HYD QTY WAS LOW.  SHORTLY AFTER THAT THE NR 2 HYD ISO VLV CAUTION LIGHT CAME ON.  ALTERNATE LANDING GEAR EXTENSION CARRIED OUT.  FOUND THE O-RING FOR THE NR 4 PLUG-BLANKING ON THE NR 2 HYDRAULIC SYSTEM MANIFOLD-FILTER HAD FAILED.  (TC NR 20061204007)                                                                                                                                                                                                                                                                                                                                                                                                                             2H72 4T    RTA13NM                        
20070129001452007012900145NM  2007       1          29         CA061204008      120061130G291082950010273     HYDRAULIC LINE                          DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  HYDRAULIC SYS   DAMAGED         W      O   OTHER                                                                                           J  WARNING INDICATION                                                            CRCRUISE         1                      CA       41474                                                          (CAN) SMALL PIN HOLE IN BEND RADIUS OF NR DIAMETER 4 TUBE ASSY, NR 1 GROUNDING ITEM IS THE HYDRUALIC LINES ON THE DASH 8`S. (TC NR 20061204008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20070126003742007012600374NM  2007       1          26         CA061205001      120061204G321310300555        YOKE                                    DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF23      NE  RT MLG          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING SCHEDULED A CHECK, RT MLG YOKE WAS FOUND TO HAVE A CRACKED FITTING AT THE AUX ACTUATOR ATTACH POINT. (TC NR 20061205001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20070129001482007012900148EA  2007       1          29         CA061205002      120061204G2750                FLAP                                    CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30015NE                              WING            MALFUNCTIONED   W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA                                                                      (CAN) AT APROX 2500-3000 FT ON FINAL APPROACH THE CREW RECEIVED A FLAP FAIL MESSAGE. THE QRH WAS FOLLOWED AND THE FLAPS WERE INDICATING AT 30 DEGREES.  THE CREW LANDED WITHOUT INCIDENT AND PERFORMED A CIRUIT BREAKER REST AND THE FLAPS RETURNED TO ZERO. FLT TO WHERE THE FLAPS OPERATED NORMALLY. (TC NR 20061205002)                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F4  FRTA21EA   E15NE                
20070129001532007012900153EA  2007       1          29         CA061205003      120061201G2750                BPSU                                    CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              T/E FLAP        OUT OF RIG      W      O   OTHER                                                                                           O  OTHER                                                                         APAPPROACH       1                      CA                                                                      (CAN) ON APPROACH THE CREW REPORTED THAT THE FLAPS WERE FAILED AT 4 DEGREES. THE AIRCRAFT WAS FERRIED WITH THE FLAPS AT 4 DEGREES. LINE MAINTENANCE COMPLETED TASK 27-51-10-830-801( RIGGING OF THE BPSU`S). BOTH WERE FOUND OUT OF RIG ALSO THE NR 7 DFECU POTENTIOMETER OUT OF RIG. ALSO THE FOLLOWING TASKS WERE COMPLETED 000-27-160-001, 000-27-160-103, 000-27-580-103, 000-27-590-001, 000-27-59-104, 000-27-680-001, 000-27-680-103,000-27-690-001 & 000-27-690-104. LT FLEX DRIVE CORE NR 1 FOUND DAMAGED AND WAS REPLACED. ALL RT AND LT FLAP ACTUATORS WERE REMOVED AND COLD SOAKED/TORQUE CHECK IAW 27-53-00-750-8011 AND SL RJ-SL-27-036. ALL ACTUATORS FOUND SERVICEABLE AND RE-INSTALLED IAW AMM 27-53-01 & 27-53-05, FUNCTION CH2L72 4F4  FRTA21EA   E15NE                
20070125001582007012500158EA  2007       1          25         CA061205004      120061204G2750                FLAP SYSTEM                             CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              TE FLAPS        MALFUNCTIONED   W      O   OTHER                                                                                           J  WARNING INDICATION                                                            APAPPROACH       1                      CA                                                                      (CAN) THE CREW REPORTED THAT ON APPROACH THEY RECEIVED THE (FLAP FAIL) CAUTION MESSAGE. ON APPROACH INTO.  CIRCUIT BREAKER RESET OF 1F4 AND 2F4 THE FLAPS RETURNED TO NORMAL FOR FLIGHT CONDITION. UPON ARRIVAL THE FLAPS WERE AT 0 DEGREES AND INSPECTED FOR BINDING OR TWISTING WITH NO FAULT FOUND. CYCLED TO 45 DEGREES WITH NFF. FECU LOG FAULT CODE FOR LEG ARE 5 1B, 5 2B, 171A, 172B, 25BC, 33 PC, FLAPS SYSTEM TESTED SERVICEABLE WITH OAT -7 DEGREES. AIRCRAFT RELEASED INTO SERVICE. (TC NR 20061205004)                                                                                                                                                                                                                             2L72 4F4  FRTA21EA   E15NE                
20070129001542007012900154NM  2007       1          29         CA061205005      120061130G3246314802OPT4      BEARING                                 DHAV  DHC8  DHC8*              NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF23      NE  MLG             FAILED          W      O   OTHER                                                                                           K  FLUID LOSS                                                                    TXTAXI/GRND HDL  1                      CA       7209                                                           (CAN) WHEN THE AC ARRIVED TO THE PARKING POSITION, A BIG HYDRAULIC LEAKAGE WAS NOTED ON THE RUNWAY. AT THE SAME TIME, MLG WHEEL NR 3 WAS FOUND TO BE DISPLACED FROM ITS NORMAL POSITION. THE WHEEL OUTER BEARING WAS FOUND DAMAGED.  RT MLG SHOCK STRUT AND WHEEL ASSY REPLACED. (TC NR 20061205005)                                                                                                                                                                                                                                                                                                                                                                                                                                            2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20070129001582007012900158GL  2007       1          29         CA061205006      320061114G6110                SHIM            HAMSTD      24PF309     DHAV  DHC7  DHC7*              EA  PWA   PT6   PT6A50      52043EA  HAMSTD24PF  24PF305     GL  PROP BLADE      BROKEN          W      O   OTHER                                                                                           WK INADEQUATE Q C            FLUID LOSS                                          ININSP/MAINT     1                      CA       4025 43                                                        (CAN) AFTER LANDING, A POST-FLIGHT INSPECTION REVEALED AN OIL LEAK IN THE NR1 PROP. FURTHER INVESTIGATION SHOWED THAT THE BLADE SHIMS HAD BEEN INSTALLED ON THE WRONG SIDE OF THE BLADE RETAINING RING. THE SHIMS HAD BROKEN AND DAMAGED THE OIL SEALS. THE OTHER 3 PROPS WERE CHECKED AND THE SAME PROBLEM WAS FOUND ALONG WITH MORE DAMAGED SEALS. (TC NR 20061205006)                                                                                                                                                                                                                                                                                                                                                                        2H74 4T4  TRTA20EA   E4EA    6  CP1NE     
20070125001622007012500162EA  2007       1          25         CA061205007      120061201G2750                FLAP SYSTEM                             CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              TE FLAPS        MALFUNCTIONED   W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA       4762 4762                                                      (CAN) DURING APPROACH WHEN FLAPS SELECTED, FLAPS REMAINED RETRACTED (0 DEG). AIRCRAFT DID FLAPLESS LANDING. ON GROUND FLAP CIRCUIT BREAKER RE-SET CARRIED OUT, FLAPS FUNCTIONED NORMALLY. AIRCRAFT DEPARTED FOR MAINTENANCE BASE FOR ADDITIONAL INSPECTIONS (TC NR 20061205007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA21EA   E15NE                
20070125001632007012500163CE  2007       1          25         CA061205008      120061205G3233AN6289D6        NUT                                     LEAR  35    35LEAR      5170600CE  GARRTTTFE731TFE7312     01518WP                              LT MLG ACTUATOR CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       14603      2324                                                (CAN) NUT ON HYDRAULIC LINE LEADING TO LT MAIN LANDING ACTUATOR FOUND CRACKED DURING DAILY INSPECTION.  THE NUT WAS REPLACED, GEAR SWINGS CARRIED OUT, AIRPLANE IS NOW SERVICEABLE. (TC NR 20061205008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  F  A10CE   E6WE                 
20070125001642007012500164EA  2007       1          25         CA061206001      120061011G2750                FLAP SYSTEM                             CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30015NE                              TE FLAPS        MALFUNCTIONED   W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA       2577725777                                                     (CAN) ON APPROACH FLAPS SELECTED TO 8 DEG, FLAP DID NOT TRAVEL AND (FLAP FAIL) MESSAGE DISPLAYED.  NORMAL FLAP ZERO LANDING .  AFTER LANDING , FLAP CIRCUIT BREAKER RESET PROCEDURE CARRIED OUT .  FLAPS INSPECTED AND NO FAULTS FOUND. FLAPS CYCLED WITH NO FAULTS FOUND. (TC NR 20061206001)                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F4  FRTA21EA   E15NE                
20070125001662007012500166EA  2007       1          25         CA061206002      120061202G5520NAS620413D      BOLT                                    CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30015NE                              LT ELEVATOR     MISINSTALLED    W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) LT ELEVATOR, FOUND NUT/BOLT COMBINATION INCORRECTLY INSTALLED ON LT NR 1 PCU JAM TOLERANT MECHANISM.  AIRFRAME HOURS: 25355:05. CYCLES: 20701. (TC NR 20061206002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F4  FRTA21EA   E15NE                
20070125001682007012500168NE  2007       1          25         CA061206003      220061202G7230                BLADES                                  CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              LT ENGINE       DAMAGED         W      O   OTHER                                                                                           E  VIBRATION/BUFFET                                                              NRNOT REPORTED   1                      CA                                                                      (CAN) UNUSUAL NOISE AND VIBRATION FROM LT ENGINE. FOUND FAN BLADES NRS: 8,9,10,11,22,23,24 AND 25 BENT AND DAMAGED.  AIRFRAME HOURS=5306:19. CYCLES=3929. (TC NR 20061206003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  FRTA21EA   E15NE                
20070125001692007012500169EA  2007       1          25         CA061206004      120061206G2750                FLAP SYSTEM                             CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              TE FLAPS        MALFUNCTIONED   W      D   RETURN TO BLOCK                                                                                 J  WARNING INDICATION                                                            TXTAXI/GRND HDL  1                      CA       1118711187                                                     (CAN) (FIRST FLIGHT OF DAY, AIRCRAFT HAD BEEN OUTSIDE ON GATE OVERNIGHT, OAT AT -20DEG OR LOWER) DURING TAXI FROM GATE UPON SELECTING FLAP TO 8DEG POSITION, (FLAPS FAIL) MESSAGE AND FLAPS FAILED TO EXTEND. AIRCRAFT RETURNED TO GATE. FLAP CIRCUIT BREAKER RE-SET PROCEDURE CARRIED OUT UNSUCCESSFUL. AIRCRAFT COMPLETELY POWERED DOWN. UPON POWER UP, FLAPS FUNCTIONED NORMAL. FLAP VISUAL INSPECTED AND FUNCTIONED SEVERAL TIMES. AIRCRAFT DEPARTED AS SCHEDULED FLIGHT. UPON FLAP SELECTION AT DESTINATION AIRPORT, FLAPS FAILED TO EXTEND, FLAP (O) LANDING CARRIED OUT. AIRCRAFT TO BE FERRIED TO MAIN MAINTENANCE BASE FOR INSPECTION. (TC NR 20061206004)                                                                             2L72 4F4  FRTA21EA   E15NE                
20070125001712007012500171CE  2007       1          25         CA061206005      120061124G2810244224152       HOSE                                    LEAR  45    45LEAR      5170805CE  GARRTTTFE731TFE7312     01518WP                              FUEL SYSTEM     LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       1266                                                           (CAN) AFTER AIRCRAFT WAS PARKED OVERNIGHT WITH FULL FUEL, A MINOR FUEL SEEP WAS DISCOVERED COMING FROM RT FUSELAGE FUEL TANK TO WING FLEX HOSE ASSY. DURING REPLACEMENT OF RT HOSE WITH FULL LT WING FUEL IT WAS DISCOVERED THE LT FUSELAGE TO WING FUEL FLEX HOSE ALSO HAD A MINOR SEEP. THIS IS ONLY NOTICEABLE WHEN THE AIRCRAFT IS SITTING FOR A FEW HOURS WITH FULL FUEL IN THE WINGS. ON INVESTIGATION OF OUR OTHER AIRCRAFT IT WAS DISCOVERED THE RT FLEX HOSE HAD THE SAME PROBLEM.  THESE ARE P/N 244224151 AND 244224152 FLEX HOSE ASSEMBLIES.  (TC NR 20061206005)                                                                                                                                                                   2L72 4F4  FRTT00008WIE6WE                 
20070125001732007012500173CE  2007       1          25         CA061207001      120061206G2897                WIRE                                    CESSNA500   550         2076604CE  PWA   JT15  JT15D4      52112NE                              FUEL CELL       DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       5877                                                           (CAN) THE FUEL TANKS SHOW EVIDENCE OF LOCALIZED DISCOLORATION AND VARIOUS NICKS ON OUTER JACKETS OF FUEL QUANTITY PROBE WIRING. THERE IS ALSO DISCOLORATION ON THE TERMINALS OF THE VARIOUS FUEL PROBES. THIS DAMAGE IS PROBABLY CAUSED BY IMPROPER USE OF THE TYRAP TOOL MOST LIKELY AT THE FACTORY LEVEL. THIS IS THE SECOND TIME THIS TYPE OF DAMAGE HAS BEEN FOUND ON A COMPANY AIRCRAFT. (TC NR 20061207001)                                                                                                                                                                                                                                                                                                                               1L72 4F4  F  A22CE   E1NE                 
20070125002612007012500261EU  2007       1          25         CA061207002      120061207G5310F10A212107      WINDOW FRAME                            AMD   FALC10FALCON10    2730101EU                                                               WINDOW          CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       6674                                                           (CAN) REMOVED FRONT WINDSHIELDS TO COMPLY WITH COCKPIT WINDOW FRAME INSPECTION REQUIREMENT OF THE C2 INSPECTION.  FOLLOWING REMOVAL OF PILOTS WINDSHIELD, SEVERE EXFOLIATION CORROSION WAS FOUND ON LOWER FRAME APPROX. 16 INCHES FROM OUTER RAIL OVER AN 8 INCH WIDTH ON THE FRAME.  (TC NR 20061207002)                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F      A33EU                        
20070129001662007012900166EU  2007       1          29         CA061207003      120061203G523017040238003     PLATE                       17040236407 EMB   ERJ170ERJ170100          EU  GE    CF34  CF348E5A1   30015NE                              CARGO DOOR      BENT            W      O   OTHER                                                                                           WP INADEQUATE Q C            NO WARNING INDICATION                               TXTAXI/GRND HDL  1                      CA       2611                                                           (CAN) ACFT WAS TAXIING TO DE-ICING BAY, WHERE THE DEICING PERSONNEL NOTICED THAT THE C1 CARGO DOOR WAS AJAR BY 2 INCHES.  MAINTENANCE WAS CALLED IN, AND THEY NOTICED THAT BOTH HANDLES WERE STOWED. THE DOOR WAS OPENED TO CHECK FOR OBSTRUCTIONS, AND FOUND THE COVER PLATE TO BE BENT.  NO OTHER DAMAGE WAS NOTED, AND THE DOOR WAS CLOSED NORMALLY.  THE GREEN INDICATION ON THE DOOR WINDOW WAS APPARENT.  THIS INFO WAS THEN PASSED ON TO THE F/O.  ALSO, THE COCKPIT INDICATION DID NOT SHOW DOOR TO BE OPENED.  CREW DID NOT REALIZE DOOR WAS OPENED.  IT IS SUSPECTED THAT THE MIDWAY LATCH WAS ROTATED BY A BENT PLATE, WHICH THEN ALLOWED THE HANDLES TO BE STOWED WITHOUT THE LATCH CAMS ENGAGED AROUND THE LATCH PINS. (TC NR2006122L72 4F4  FRTA56NM   E00063EN             
20070129001682007012900168SW  2007       1          29         CA061207004      120061207G79218543909         OIL COOLER                              BELL  206   206L1       1182107SW  ALLSN 250C  250C28B     03013GL                              ENGINE          LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA                                                                      (CAN) ON AIRCRAFT RETURNING TO BASE IT WAS NOTED THAT THERE WAS OIL ON THE TAILBOOM. ON INVESTIGATION THE SOURCE OF THE OIL WAS FOUND TO BE THE OIL COOLER. COOLER CHANGED. (TC NR 20061207004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1G71 3U3  U  H2SW    E1GL                 
20070129001792007012900179SO  2007       1          29         CA061207005      120061206G8011                DRIVE GEAR                  MHB4014R    PIPER PA31  PA31350     7103110SO  LYC   O540  TIO540J2BD  41532EA  HARTZLHCE3Y HCE3YR2A    GL  STARTER         DESTROYED       W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA            1926  C120571                                             (CAN) WHILE AIRCRAFT WAS AWAY FROM BASE ON A SCHEDULED RUN THE CREW WAS ATTEMPTING TO STAR THE NR 2 ENGINE. THEY NOTED NO ENGAGEMENT OF THE STARTER (ENGINE DID NOT TURN OVER). A MAINTENANCE CREW WAS DISPATCHED TO REPAIR THE AIRCRAFT, WHEN THE COWLINGS WERE REMOVED SEVERAL PIECES OF METAL WERE OBSERVED. UPON REMOVAL OF THE STARTER IT WAS DISCOVERED THAT THE ENGAGEMENT GEAR ON THE BENDIX DRIVE HAD DISINTIGRATED, DAMAGING THE DRIVE HOUSING AS THE PIECES DEPARTED. THE STARTER WAS LESS THAN 80 HRS FROM OVERHAUL. AFTER DISCUSSION WITH THE CREW, THEY STATED THEY DID NOT DOUBLE TAP THE START SWITCH. AN INVESTIGATION IS STILL IN PROGRESS. (TC NR 20061207005)                                                               1L72 3O3  O  A20SO   E14EA   5  CP33EA    
20070129001812007012900181EA  2007       1          29         CA061208001      120061206G275220222788        ACTUATOR                                CNDAIRCL601 CL6013A     8070802EA  GE    CF34  CF343A      30015NE                              T/E FLAP        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       4684                                                           (CAN) DURING SCHEDULE LUBRICATION OF THE FLAP ACTUATORS, THE TECHNICIAN NOTICED GREASE WAS OOZING OUT OF A CRACKED WELD ON THE HOUSING OF THE LT OB FLAP ACTUATOR JACK SCREW. (TC NR 20061208001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F4  FRTA21EA   E15NE                
20070202001222007020200122SW  2007       2          2          CA061208003      120061205G634022A656          TACH GENERATOR                          BELL  206   206L4       1182110SW  ALLSN 250C  250C30P     03013GL                                              WORN            W      H   DEACTIVATE SYST/CIRCUITS                                                                        O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) GREASE FOUND WASHED OUT CAUSING PREMATURE WEAR OF DRIVE SPLINES LEADING TO HYDRAULIC SYSTEM FAILURE.  298.7 HRS SINCE PREVIOUS LUBRICATION. (TC NR 20061208003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1G71 3U3  UNCH2SW    E1GL                 
20080219001392008021900139SW  2008       2          19         CA061208004      120061205G2913206076030111    PUMP                                    BELL  206   206L4       1182110SW  ALLSN 250C  250C30P     03013GL                              HYDRAULIC SYSTEMLACK OF LUBE    W      H   DEACTIVATE SYST/CIRCUITS                                                                        F  FLT CONT AFFECTED                                                             CRCRUISE         1                      CA                                                                      (CAN) GREASE FOUND WASHED OUT CAUSING PREMATURE WEAR OF DRIVE SPLINES LEADING TO HYDRAULIC SYSTEM FAILURE. 198.3 HRS SINCE PREVIOUS LUBRICATION. (TC NR 20061208004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1G71 3U3  UNCH2SW    E1GL                 
20070129001822007012900182NE  2007       1          29         CA061208005      220061203G72309324M70G06      COMPRESSOR                              AIRBUSA340  A340313            EU  CFMINTCFM56 CFM565C4    13802NE                              ENGINE          STALLED         W      E   ENGINE SHUTDOWN                                                                                 ME OVER TEMP                 VIBRATION/BUFFET                                    CRCRUISE         1                      CA       299614857                                                      (CAN) IN CRUISE, 2 HOURS FROM DESTINATION THE ENGINE STALLED AND EGT WAS RISING.  WHEN EGT REACHED 1010 DEG. C, THE ENGINE WAS SHUTDOWN. THE OIL PRESSURE WENT TO ZERO AND BOTH N1 AND N2 ROTORS WERE ROTATING.  DFDR DATA SHOWS: N2 VIBRATION WAS HIGH (3.5 TO 5.5 UNITS) AFTER THE STALL, RAPIDLY REDUCED TO 2.O UNITS AND THEN SLOWLY REDUCED TO ZERO BEFORE ENGINE SHUTDOWN.  N1 VIBRATION WAS LOW AFTER THE STALL (0.5-2 UNITS) AND RAPIDLY INCREASED AFTER STALL TO 5-5.5 UNITS AND STAYED THERE.  N1, N2, FUEL FLOW HAD A RAPID DECREASE AFTER THE STALL AND RECOVERED SLIGHTLY, THEN SLOWLY DECREASED WITH EGT RISING.  AFTER AIRCRAFT LANDED, BASE MAINTENANCE CARRIED OUT A VISUAL INSPECTION WITH THE FOLLOWING FINDINGS: NO DAMAGE O2L74 4F4  FRTA197    E37NE                
20070129001832007012900183EA  2007       1          29         CA061211001      120061203G5610NP13932100      WINDSHIELD                              CNDAIRCL600 CL6002C10   1390015EA                                                               COCKPIT         CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA                                                                      (CAN) RT SIDE WINDSHIELD SHATTERED (TC NR 20061211001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA21EA                        
20070129001842007012900184EA  2007       1          29         CA061211002      120061203G5610601R3303311     WINDOW                                  CNDAIRCL600 CL6002B19   1900309EA                                                               COCKPIT         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA                                                                      (CAN) LT SIDE WINDOW SHATTERED. (TC NR 20061211002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F    RTA21EA                        
20070129001852007012900185    2007       1          29         CA061211003      420061210G34177000700940      ADC                                     DHAV  DHC8  DHC8*              NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF23      NE  NR 2            MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 G  MULTIPLE FAILURE                                                              CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE, THE F/O ALTIMETER OFF FLAG CAME INTO VIEW ON NUMEROUS OCCASSIONS. THE EGPWS FAULT LIGHT ALSO ILLUMINATED.  PILOT ELECTED TO PERFORM AN AIR TURN BACK.  NR 2 DIGITAL AIR DATA COMPUTER REPLACED. (TC NR 20061211003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20070129001862007012900186EA  2007       1          29         CA061211004      120061207G7120601370541       PLUG            CNDAIR      ASB1810617  CNDAIRCL600 CL6002B19   1900309EA                                                               LT ENGINE       MISSING         W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA                                                                      (CAN) DURING OF C-CHECK INSPECTION FOUND THAT PLUG ASSY P/N 60137054-1 IS NOT INSTALLED AT THE AFT ENGINE TRUST FITTING P/N ASB18106-17 OF LT ENGINE. TO INSTALL THE PLUG ENGINE NEED TO BE REMOVED. (TC NR 20061211004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F    RTA21EA                        
20070125001862007012500186NE  2007       1          25         CA061211005      320061207G611114SF23          BEARING RACE                            DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE  HAMSTD14SF  14SF23      NE  NR 1 PROP       FRACTURED       W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         E  VIBRATION/BUFFET                                                              CRCRUISE         1                      CA       24284                                                          (CAN) LIGHT TO MODERATE PROP VIBRATION IN CRUISE, AS POWER WAS REDUCED FOR DESCENT VIBRATION BECAME EXCESSIVE.  AS A RESULT THE NR 1 PROP (CONDITION LEVER) WAS SELECTED TO START FEATHER (VIBRATION STOP) AND THEN NR 1 ENGINE WAS SHUTDOWN.  ALL ENGINE PARAMETERS WERE NORMAL PRIOR TO SHUTDOWN.  FOLLOWING THE IFSD AS DESCRIBED ABOVE, MAINTENANCE PERFORMED A LOW POWER RUN TO VERIFY THE VIBRATION AS REPORTED. THE VIB WAS CONFIRMED AND THE ENGINE SHUTDOWN.  OIL WAS THEN NOTED DRIPPING FROM THE VICINITY OF THE NR 1 PROP.  INITIAL INVESTIGATION HAS REVEALED THAT THE NR 1 PROP, NR 4 BLADE BEARING RACE HAS FRAGMENTED INTO SEVERAL PARTS. (TC NR 20061211005)                                                                   2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20070125002092007012500209EA  2007       1          25         CA061211006      120061203G493038301552        LINE            HONEYWELL               CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30015NE                              FUEL MANIFOLD   BROKEN          W      O   OTHER                                                                                           KB FLUID LOSS                SMOKE/FUMES/ODORS/SPARKS                            APAPPROACH       1                      CA       1526815268 P365C                                               (CAN) RT AIR CONDITIONING PACK WAS DEFERRED AND CREW HAD TO SHUTDOWN APU ON APPROACH BECAUSE OF OIL/FUEL ODOR IN THE CABIN.  CREW REPORTED A PRESSURE BUMP WHEN APU WAS SHUTDOWN.  APU WAS SUSPECTED TO BE OVER SERVICED, BUT EVEN AFTER DRAINING A LITRE OF OIL APU WOULD NOT RE-START.  FURTHER TROUBLESHOOTING FOUND THE PRIMARY FUEL MANIFOLD LINE BROKEN.  ONCE REPLACED APU OPERATED SERVICEABLE. (TC NR 20061211006)                                                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA21EA   E15NE                
20070125002122007012500212    2007       1          25         CA061211007      420061209G22117003974730      COMPUTER        HONEYWELL               DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  FLIGHT GUIDANCE FAULTED         W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA       3871815860 90012118                                            (CAN) LEVELING OFF AT 4000 FT, AFCS FAILED, ID802 SHOWED LINES, YD AND FLIGHT DIRECTOR FAILED, CAPT AND F/O ADI`S FLAGGED OFF. AIRCRAFT RETURNED TO ORIGINATING AIRPORT FOR NORMAL LANDING.  MAINTENANCE INSPECTION OF FLIGHT FAULT SUMMARY SHOWED FAILURE OF RIGHT FLIGHT GUIDANCE COMPUTER. COMPUTER REPLACED AND FUNCTION CHECKED. AIRCRAFT RETURNED TO SERVICE. (TC NR 20061211007)                                                                                                                                                                                                                                                                                                                                                         2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20070125002142007012500214SW  2007       1          25         CA061211008      120061208G293227191543        TRANSDUCER                              SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE33111U   01514WP  MCAULY4HFR344HFR34C652  NE  HYD PRESS TRANS SPLIT           W      O   OTHER                                                                                           J  WARNING INDICATION                                                            LDLANDING        1                      CA                                                                      (CAN) AIRCRAFT LOST HYD PRESSURE ON LANDING.  THERE WAS NO INDICATION OF PRESSURE ON GAUGE AND ON THE ANUNCIATOR PANEL.  HYDRAULIC PRESSURE TRANSDUCER FOUND SPLIT AROUND HYDRAULIC FITTING END.  TRANSDUCER AND SHUTTLE VALVE WERE REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20061211008)                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4T4  TRTA8SW    E4WE    6  C3PNE     
20070125002152007012500215NM  2007       1          25         CA061211009      120061209G5610141A481014      WINDOW                                  BOEING737   73776N      13844CHNM  CFMINTCFM567CFM567B22   13802NE                              COCKPIT         CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA       19028                                                          (CAN) WINDOW FLT COMPARTMENT DELAMINATED, CRACKED NR 2 LT DESCENDED TO FL210 + INC CABIN ALT TO 9000 FT, WHICH GAVE US A CABIN DIFF OF 3.6 PSI.  CAPT`S NR 2 SLIDING WINDOW REPLACED IAW AMM 56-12-11, GND CHECKED SERVICABLE. COCKPIT WINDOW FAILURES ARE PART OF A SAFETY RELATED SERVICE PROBLEM SRP 56-0018 WITH MFG.  ICA ISSUANCE IS AWAITED FOR PERMANENT RECOMMENDED ACTION. (TC NR 20061211009)                                                                                                                                                                                                                                                                                                                                        2L72 4F4  FRTA16WE   E00055EN             
20070125002182007012500218EA  2007       1          25         CA061212001      220061210G7200                ENGINE                                  EMB   110   EMB110P1    3260122SO  PWA   PT6   PT6A34      52043EA  HARTZLHCB3T HCB3TN3     GL  RIGHT           FAILED          W      FA  ACTIVATE FIRE EXT.      UNSCHED LANDING                                                         XA ENGINE FLAMEOUT           FLAME/FIRE                                          DEDESCENT        1                      CA       20124214                           42129                       (CAN) SHORTLY AFTER COMPLETING THE DESCENT CHECKS FOR A LANDING (WITH ENGINES OPERATING NORMALLY, ENGINE INSTRUMENTS IN THE GREEN, THE CREW HEARD A LOUD NOISE FOLLOWED BY A SUDDEN LOSS OF POWER ON THE RT ENGINE. IMMEDIATELY FOLLOWING THE SUDDEN LOSS OF POWER THE RT ENGINE CAUGHT ON FIRE. THE PROCEDURES FOR AN IN-FLIGHT ENGINE FIRE WERE CARRIED OUT AND THE FIRE WAS EXTINGUISHED. AFTER INITIAL INSPECTION THE CAUSE OF THE ENGINE FAILURE WAS DUE TO AN INTERNAL FAILURE OF THE ENGINE. ITEMS NOTICED DURING INITIAL INSPECTION ARE AS FOLLOWS: POWER SECTION SEIZED, OIL VISIBLE IN BOTH EXHAUST STACKS, NO EXTERNAL INDICATION OF FIRE DAMAGE TO ENGINE VISIBLE (FIRE WAS LIMITED TO EXHAUST STACKS DUE TO OIL LOSS FROM INTERNAL 1L72 4T4  T  A21SO   E4EA    6  CP15EA    
20070125002192007012500219SO  2007       1          25         CA061212002      120061112G6100                PROPELLER                               LKHEED382   382G        526414USO  ALLSN 501D  501D22A     03006GL  HAMSTD54H   54H60117    NE  NR 4            DAMAGED         W      E   ENGINE SHUTDOWN                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) IN CRUISE AT FL240 AFTER DEPARTURE THE CREW OBSERVED LOW OIL QTY ON NR 2 ENGINE. THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT CONTINUED TO DESTINATION.  SHORTLY AFTER RE-ESTABLISHING  CRUISE AT FL220 THE CREW OBSERVED LOW OIL QTY ON NR 4 PROPELLER. THE PROP WAS SELECTED TO MECHANICAL GOVERNING AND THE AIRCRAFT CONTINUED TO DESTINATION. THE NR 4 ENGINE WAS SHUTDOWN ON DESCENT TO PRECLUDE PROP OVERSPEED. THE AIRCRAFT ARRIVED WITHOUT FURTHER PROBLEMS. MAINTENANCE REPLACED THE NR 2 ENGINE SCAVENGE FILTER AND THE NR 4 PROPELLER ASSY. AIRCRAFT SATISFACTORILY GROUND RUN AND RETURNED TO SERVICE.                                                                                                                            2H74 4T4  T  A1SO    E282    6  CP906     
20070125002202007012500220NM  2007       1          25         CA061212003      120061211G75008209074         SWITCH                                  BOMBDRDHC8  DHC8402     1390042NM                                                               RT NACELLE      FAILED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            APAPPROACH       1                      CA       40                                                             (CAN) NR 2 BLEED HOT CAUTION LIGHT COME ON 4 MILES OUT.  CDS INTEROGATION FAULT CODES 7005, 7001 AND 1701. (TC NR 20061212003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2H72 4T    RTA13NM                        
20070125002212007012500221EA  2007       1          25         CA061212004      120061202G5610NP13932111      WINDSHIELD                              CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30015NE                              COCKPIT         CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA       3695 3695                                                      (CAN) DURING CRUISE CAPTAINS FRONT WINDSHIELD SHATTERED. (NO PRESSURIZATION LOSS).  CREW DECLARED EMERGENCY AND DESCENDED TO 10000 FT AND DIVERTED TO NEAR BY ALTERNATE AIRPORT.  MAINTENANCE REPLACED WINDSHIELD AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20061212004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F4  FRTA21EA   E15NE                
20070125002232007012500223SO  2007       1          25         CA061212005      120061210G291365WE002241      PUMP                                    EMB   110   EMB110P1    3260122SO  PWA   PT6   PT6A34      52043EA  HARTZLHCB3T HCB3TN3     GL  HYDRAULIC       FAILED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            APAPPROACH       1                      CA                                                                      (CAN) (5) MINUTES AFTER AN ENGINE FAILURE OF THE RT ENGINE (SDR 20061212001) THE HYDRAULIC LIGHT CAME ON EVEN THOUGH THE LT ENGINE WAS OPERATING NORMALLY. THE CREW ATTEMPTED TO EXTEND THE LANDING GEAR NORMALLY BUT IT WOULD NOT LOCK. THE GEAR WAS THEN SUCCESSFULLY HAND PUMPED DOWN.  A FAILURE OF THE LT ENGINE DRIVEN HYDRAULIC PUMP IS SUSPECTED TO BE THE CAUSE OF NOT BEING ABLE TO EXTEND THE LANDING GEAR NORMALLY.  THE HYDRAULIC PUMP WILL BE REMOVED AND SENT OUT FOR A TEARDOWN. (TC NR 20061212005)                                                                                                                                                                                                                            1L72 4T4  T  A21SO   E4EA    6  CP15EA    
20070125002632007012500263NM  2007       1          25         CA061212006      120061212G323054C546349       SEQUENCE VALVE                          DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  MLG             RUPTURED        W      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) UPON RETRACTION OF THE LANDING GEAR THE CREW HEARD A STRANGE NOISE FOLLOWED BY HYDRAULIC FLUID QUANTITY LOSS IN THE NR 2 SYSTEM. THE CREW CARRIED OUT THE APPLICABLE PROCEDURES TO EXTEND THE LANDING GEAR BUT WERE NOT ABLE TO GET THE NOSE LANDING GEAR TO EXTEND. THE CREW FLEW THE AIRCRAFT FOR SEVERAL HOURS TO BURN OFF FUEL AND TRY TO GET THE NOSE GEAR TO EXTEND BUT WERE UNSUCCESSFUL AND COMPLETED A NOSE GEAR RETRACTED LANDING ON A SNOW PACKED RUNWAY. THE AIRCRAFT WAS SUBSEQUENTLY DAMAGED IN THE NOSE LANDING GEAR DOOR AND RADOME AREAS. UPON INITIAL INVESTIGATION BY MAINTENANCE IT WAS FOUND THAT THE LT MLG DOOR SEQUENCING SOLENOID VALVE WAS RUPTURED CAUSING THE LOSS OF THE NR 2 HYDRAULIC SYSTEM FLUID.  IT IS 2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20070125002252007012500225WP  2007       1          25         CA061212007      220061030G7250310210610       TURBINE WHEEL                                                              GARRTTTPE331TPE33110U   01514WP                              NR 2            DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       1122                                                           (CAN) FOUND UPON DOING A HSI INSPECTION THAT THE NR 2 ROTOR THE RIVETS WERE FOUND LOOSE TO THE POINT THAT THEY WERE GOING TO START COMING OUT. THIS WHEEL IN QUESTION ONLY HAD 1409 CYCLES TOTAL ON IT. (TC NR 20061212007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            4  T          E4WE                 
20070125002282007012500228WP  2007       1          25         CA061212008      220061212G7250310210610       TURBINE WHEEL               310210610                                      GARRTTTPE331TPE33110UA  01514WP                              ENGINE          DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3598                                                           (CAN) FOUND UPON INSPECTION AT THE HSI INSPECTION THAT THE RIVETS WERE LOOSE AND DEFORMED TO THE POINT THAT THE RIVETS WERE GOING TO COME OUT AND POSSIBLY WOULD CAUSE MORE DAMAGE INSIDE THE ENGINE. (TC NR 20061212008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              4  T          E4WE                 
20070125002302007012500230EA  2007       1          25         CA061212009      120061121G2750                FLAP SYSTEM                             CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              TE FLAPS        MALFUNCTIONED   W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA       1159311593                                                     (CAN) ON APPROACH WHEN FLAPS SELECTED, (FLAP FAIL) MESSAGE AND FLAPS REMAINED AT ZERO DEG., FLAPLESS LANDING. ON GROUND FLAP CIRCUIT BREAKERS RESET PROCEDURE CARRIED OUT, FLAPS FUNCTION CHECKED NORMAL. (TC NR 20061212009)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F4  FRTA21EA   E15NE                
20070125002312007012500231EU  2007       1          25         CA061213001      120061210G521019017111401     DOOR                                    EMB   ERJ190ERJ190100IGW3260408EU  GE    CF34  CF34*            NE                              COCKPIT         DISLODGED       W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA       250                                                            (CAN) FLIGHT DECK DOOR CAME FREE ON FRAME WHEN OPENED FROM CABIN SIDE IN FLIGHT.  BOTTOM LOCATING PIN FOUND BENT AND TEMPORARILY FIXED.  TOP PIN DOES NOT REMAIN IN FRAME BRACKET.  DOOR SERVICEABLE FOR REMAINDER OF FLIGHT ONLY. (TC NR 20061213001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA57NM   E15NE                
20070125002332007012500233EA  2007       1          25         CA061213002      120061208G262013739002        SWITCH                                  CNDAIRCL600 CL6002B19   1900309EA                                                               EXTINGUISHER    JAMMED          W      K   NONE                                                                                            L  NO TEST                                                                       ININSP/MAINT     1                      CA                                                                      (CAN) BOTH CARGO FIRE X-BOTTLES DISCHARGED WHEN , NORMAL CARGO SMOKE PUSH) SWITCH-LIGHT ACTUATED TO ARM THE DISCHARGE SQUIBS. AFTER INVESTIGATION FOUND THAT BOTTLE ARMED (PUSH TO DISCHARGE) SWITCH-LIGHT JAMMED IN THE (PUSH) POSITION. (TC NR 20061213002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F    RTA21EA                        
20070129001872007012900187EA  2007       1          29         CA061213003      120061208G261213739002        LIGHT           BOMBDR      601R5107083 CNDAIRCL600 CL6002B19   1900309EA                                                               FIRE WARNING    INTERMITTENT    W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) DUE TO INCIDENT, CARGO FIREX PANEL TESTED AND FOUND THAT (NORMAL BOTTLE ARMED PUSH TO DISCH) SWITCH-LIGHT IS INTERMITTENT OR JAMMED IN THE CLOSE POSITION. (TC NR 20061213003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F    RTA21EA                        
20070129001882007012900188EA  2007       1          29         CA061213004      120061208G261213739002        LIGHT           CNDAIR      601R5107083 CNDAIRCL600 CL6002B19   1900309EA                                                               FIRE WARNING    INTERMITTENT    W      O   OTHER                                                                                           O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DUE TO INCIDENT ON AC N639BR, CARGO  FIREX PANEL TESTED AND FOUND THAT (NORMAL BOTTLE ARMED PUSH TO DISCH) SWITCH-LIGHT IS INTERMITTENT OR JAMMED IN CLOSE POSITION. (TC NR 20061213004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F    RTA21EA                        
20070129001892007012900189NM  2007       1          29         CA061213005      120061210G792128E997          OIL COOLER                              DHAV  DHC8  DHC8102     2809003NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  ENGINE          CRACKED         W      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA            301                                                       (CAN) OIL COOLER SEAM WELD CRACKED DURING FLIGHT ALLOWING LEAKAGE AND LOW ENGINE OIL PX. (TC NR 20061213005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20070125002352007012500235EA  2007       1          25         CA061214001      120061213G2750                FLAP SYSTEM                             CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30015NE                              TE FLAPS        MALFUNCTIONED   W      O   OTHER                                                                                           O  OTHER                                                                         APAPPROACH       1                      CA                                                                      (CAN) ON APPROACH THE CREW SELECTED FLAP 40 AND THE FLAPS FAILED AT 20 DEGREES. THE AIRCRAFT LANDED WITHOUT INCIDENT AND WAS LATER FERRIED WHERE IT IS CURRENTLY UNDERGOING INSPECTION. (TC NR 20061214001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA21EA   E15NE                
20070125002372007012500237SO  2007       1          25         CA061214002      220061207G7314                SEAL                                    DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO  SNSNCHW69EK W69EK63     EA  FUEL PUMP       LEAKING         W      O   OTHER                                                                                           R  PARTIAL RPM/PWR LOSS                                                          NRNOT REPORTED   1                      CA       1337                                                           (CAN) AIRCRAFT BROUGHT IN FOR 50 HR.MAINTENANCE CHECK FOUND FUEL ON BOTTOM OF COWL AND IT WAS TRACED BACK TO THE ENGINE DRIVEN FUEL PUMP. THE SEALS IN THE FUEL PUMP HAD STARTED TO FAIL OR HAD FAILED AROUND THE MIXTURE CONTROL LEVER ASSY. THE TOP COVER ALSO WAS LEAKING FUEL. FUEL PUMP WAS REMOVED AND SENT FOR REPAIRS. UNIT REPAIRED AND RELEASED ON 24-0078  NR A47159 (TC NR 20061214002).                                                                                                                                                                                                                                                                                                                                            1L71 3O3  ONTTA4CH   E7SO    5  NTA4CH    
20070125002392007012500239EU  2007       1          25         CA061214003      120061129G3010                BOOT                                    PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  DEICE SYSTEM    SPLIT           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       6085 6085                                                      (CAN) AIRCRAFT RETURNED FROM FLIGHT TO ARCTIC.  ALL DE-ICE BOOTS ON AIRCRAFT WERE FOUND SPLIT ALONG CHORD AND HAD TO BE REPLACED.  THE PRESSURE REGULATOR WAS TESTED AND FOUND TO BE FUNCTIONING NORMAL.  WE WERE UNABLE TO DETERMINE THE CAUSE OF THE FAILURE.  THE PILOT REPORTED IT WAS COLD AT ALTITUDE AND NOT SURE IF THE BOOTS WERE ACTIVATED.  (TC NR 20061214003)                                                                                                                                                                                                                                                                                                                                                                      1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20070129001902007012900190NE  2007       1          29         CA061214004      220061214G72305009T34P01      BLADE           GE          5012T75624                                     GE    CT58  CT581402    30011NE                              COMPRESSOR      MISSING         W      O   OTHER                                                                                           R  PARTIAL RPM/PWR LOSS                                                          ININSP/MAINT     1                      CA            893   HAAH2079                                            (CAN) RECEIVED THIS ENGINE WITH A DEFECT OF LOW POWER. IT WAS RUN ON THE TEST STAND TO CONFIRM THE POWER OUTPUT WHICH WAS 1440 SHP.  WHEN THE ENGINE WAS DISASSEMBLED THEY FOUND THAT A BLADE WAS MISSING FROM THE COMPRESSOR 4TH STAGE.  THERE WAS NO DAMAGE TO THE FIRST 3 SECTIONS BUT IT RESULTED IN DAMAGING THE DOWNSTREAM BLADES AND VANES. THE 4TH STAGE BLADES ARE CURRENTLY AT INVESTIGATIION. THIS ENGINE IS OWNED BY OPERATOR AND A COPY OF THIS SDR WILL BE SUBMITTED.  THERE IS MORE INFORMATION TO FOLLOW.  THE OWNER OF THE ENGINE IS HELI-ONE AND IT WAS BEING OPERATED ON A POWER BY THE HOUR PROGRAM. (TC NR 20061214004)                                                                                                           4  U          1E3                  
20070125002412007012500241GL  2007       1          25         CA061215001      220061202G7261                FILTER                                  LKHEED382   382G        526414USO  ALLSN 501D  501D22A     03006GL  HAMSTD54H   54H60117    NE  SCAV PUMP       UNKNOWN         W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         KJ FLUID LOSS                WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) ON DEPARTURE, THE CREW OBSERVED NR 2 ENGINE OIL LEVEL DROPPING TO 2.75 GAL. WITH A LOW OIL LIGHT ILLUMINATED. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE. MAINTENANCE REPLACED THE NR 2 SCAVENGE OIL FILTER AND REPLENISHED THE OIL QUANTITY TO 10 GAL. THE AIRCRAFT WAS FOUND SATISFACTORY AND RETURNED TO SERVICE. (TC NR 20061215001)                                                                                                                                                                                                                                                                                                                                                                                                 2H74 4T4  T  A1SO    E282    6  CP906     
20070125002422007012500242CE  2007       1          25         CA061215002      120061212G5520115520219       HINGE           BEECH                   BEECH 100   100BEECH    1152916CE  GARRTTTPE331TPE3316252B 01514WP  HARTZLHCB4T HCB4TN5     GL  ELEVATOR        DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       9051       BE114A                                              (CAN) DURING PHASE NR 2 INSPECTION, IT WAS NOTICED THAT THE LT ELEVATOR WAS LOOSE AT THE OB HINGE.  AREA INSPECTED AND FOUND THAT THE 4 BOLTS THAT ATTACH THE HINGE TO THE HORIZONTAL STAB WERE LOOSE. THE HINGE WAS REMOVED AND FOUND THAT THE HOLES WERE ELONGATED. THE HINGE AND ATTACHING STRUCTURE WERE REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                          1L72 3T4  T  A14CE   E2WE    6  CP40EA    
20070125002432007012500243    2007       1          25         CA061216001      420061214G3100A6611           IGNITION SWITCH                         ROBSINR44   R44RAVENII  7640122WP  LYC   O540  IO540AE1A5  41530NE                              INSTRUMENT PANELOBSTRUCTED      W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) REPLACED IGNITION SWITCH DURING 2200 HR O/H AND REINSTALLED IN INSTRUMENT PANEL.  THE SEATING OF THE SWITCH STOPPED THE CONSOLE FROM OPENING AGAIN.  THE SWITCH WAS REMOVED AND RESEATED TO ALLOW TRAVEL PAST THE INSTRUMENT CONSOLE.  WE COULD NOT ALIGN THE SWITCH TO PREVENT THE TERMINAL (RT MAG CONNECTION) FROM CONTACTING THE SIDE WALL OF THE LOWER CONSOLE. THE TERMINAL ONLY MAKES CONTACT DURING THE TRANSITION FROM OPEN TO CLOSE AND VICE-VERSA.  ONCE THE CONSOLE IS CLOSED THERE IS NO CONTACT OF THE TERMINAL, SIDEWALL OR LIP. WE ARE TALKING WITH MFG TO SEE IF THERE MAYBE A FIX.  COULD BE IGNITION SWITCH MAYBE HAVE TO BE DESIGNED A LITTLE SMALLER OR MORE ROOM ON PANEL. (TC NR 20061216001)                      1G71 3O3  O  H11NM   1E4                  
20070125002442007012500244CE  2007       1          25         CA061216002      120061215G32421013810127      VALVE                                   BEECH 300   300BEECH    1152930CE  PWA   PT6   PT6A60A     52043NE  HARTZLHCB4M HCB4MP3     GL  LANDING GEAR    FALSE INDICATIONW      K   NONE                                                                                            N  FALSE WARNING                                                                 ININSP/MAINT     1                      CA       28                                                             (CAN) NEW VALVE WAS INSTALLED. LANDING GEAR VALVE FAILS TO INDICATE THAT IT IS OPEN WHEN SELECTED. VALVE WORKS CORRECTLY, BUT FAILS TO INDICATE TO CREW THAT IT IS WORKING. SEEMS TO BE JUST AN ISSUE WITH THE INDICATION SIDE OF THE VALVE AND NOT THE ACTUAL MECHANICS. (TC NR 20061216002)                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4T4  T  A24CE   E4EA    6  CP56GL    
20070125002452007012500245NM  2007       1          25         CA061216003      120061212G2910BACH8C08NN0290  LINE                                    BOEING727   727243      138408DNM                                                               HYD SYSTEM      LEAKING         W      A   UNSCHED LANDING                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) AFTER T/O DURING CLIMB (B) PUMP LOW PX LITE ILLUMINATED WITH FLUID QTY DROP.  RETURNED TO DEPARTURE, HYD LINE REPLACED IN B COMPT.  (TC NR 20061216003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L73 4F    RTA3WE                         
20070125002462007012500246SO  2007       1          25         CA061217001      120061216G32104025700         TORQUE LINK                             PIPER PA31  PA31        7103102SO  LYC   O540  TIO540A1B   41532EA  HARTZLHCE2Y HCE2YR2     GL  RT MLG STRUT    BROKEN          W      O   OTHER                                                                                           O  OTHER                                                                         LDLANDING        1                      CA                                                                      (CAN) THE PILOT REPORTED NOTICING A VIBRATION DURING TAXI BUT ATTRIBUTED IT TO RUNWAY CONDITION.  IN FLIGHT HE WAS UNABLE TO RETRACT THE LANDING GEAR. UPON LANDING HE WAS UNABLE TO EXECUTE TURNS.  AFTER DEPLANING HE FOUND THE FORWARD LUG ON THE UPPER TORQUE LINK OF THE RT MLG BROKEN.  THE TORQUE LINK ASSEMBLY WAS HELD IN PLACE ONLY BY THE BOTTOM TORQUE LINK ATTACH BOLT. THE BOLT THAT ATTACHES THE UPPER TORQUE LINK WAS MISSING ALONG WITH THE BROKEN LUG.  A CAUSE COULD NOT BEEN DETERMINED.  THE AIRCRAFT WAS TOWED TO THE HANGER. (TC NR 20061217001)                                                                                                                                                                         1L72 3O3  O  A20SO   E14EA   5  CP9EA     
20070125002472007012500247EA  2007       1          25         CA061218001      120061216G2750855D1009        BPSU                                    CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              TE FLAPS        FAILED          W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA                                                                      (CAN) THE CREW REPORTED THAT CLIMBING THROUGH FL220  (FLAP FAILED) MESSAGE CAME ON. THE CREW ELECTED TO CONTINUE AND THE FLIGHT LANDED WITHOUT FURTHER INCIDENT.  LINE MAINTENANCE FOUND THE FOLLOWING FAULT CODES 1-12-2B RH BPSU. FECU TEST CARRIED OUT NFF. WIRING BETWEEN FECU AND BPSU COMPLETED. BPSU REMOVED, NEW ONE INSTALLED AND RIGGED IAW AMM 27-51-10 FLAPS FUNCTION CHECKED SEVERAL TIMES AIRCRAFT RELEASED FOR SATISFACTORY TEST FLIGHT THEN RELEASED INTO SERVICE.                                                                                                                                                                                                                                                              2L72 4F4  FRTA21EA   E15NE                
20070125002482007012500248EA  2007       1          25         CA061218002      220061126G7414K3823           BRUSH BLOCK     SLICK                   FOUND FBA   FBA2C       3640102EA  LYC   O540  IO540*      41532EA  HARTZLHCC3Y HCC3YR      GL  MAGNETO         WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       587        05061176                                            (CAN) THE DISTRIBUTOR GEAR BRUSH WAS EXCESSIVELY WORN FOR HAVING 587.2 HOURS ON IT IN A COMPONENT DESIGNED WITH A 2000 HOUR TBD. BRUSH BUSHING AND MOUNT OF POOR QUALITY WHICH IF LEFT UNDETECTED WOULD RESULT IN FAILURE IN 2 OR 300 MORE HOURS IF BEARING AND BUSHING AND BRUSH. (TC NR 20061218002)                                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3O3  O  A7EA    1E4     5  CP25EA    
20070125002492007012500249SO  2007       1          25         CA061218003      220061106G7414K3823           DISTRIBUTOR GEARSLICK                   CESSNA206   U206F       2073333CE  CONT  O520  IO520F      17032SO  HARTZLHCC3Y PHCC3YF1    GL  MAGNETO         BURNED          W      C   ABORTED TAKEOFF                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  TOTAKEOFF        1                      CA       727        05012258                                            (CAN) DURING RUNUP AND PRE-TAKE OFF THE PILOT OBSERVED LARGE MAG DROPS AND POWER FLUCTUATIONS. THE AIRCRAFT WAS BROUGHT INTO THE SHOP. THE MAGNETOS WERE REMOVED AND INSPECTED.  UPON INSPECTION, IT WAS DISCOVERED BOTH DISTRIBUTOR BLOCK AND GEAR HOUSINGS WERE BURNED THRU AT THE BRUSH HOLDER.  ONE BRUSH WAS MISSING. THE COIL WAS ARCING THRU TO THE MAGNET.  INVESTIGATION DETERMINED THE BUSHINGS AND DISTRIBUTOR GEAR BRUSH HAS WORN ABNORMALLY.  THE BUSHINGS GOT VERY LOOSE CAUSING THE SECONDARY BRUSH TO WEAR AND ARC. THE DISTRIBUTOR GEAR AND HOUSING ARE PLASTIC. THE PLASTIC MELTED AND BOTH MAGS WERE ABOUT TO TOTALLY FAIL, DO NOT KNOW HOW IT KEPT RUNNING.                                                                 1H71 3O3  O  A4CE    E5CE    5  CP25EA    
20070125002532007012500253EU  2007       1          25         CA061218004      120061120G79300292005340      ENGINE                                  SNIAS 350   AS350B3     8680954EU  TMECA ARRIELARRIEL2B         NE                                              MAKING METAL    W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA       779                                22364                       (CAN) AIRCRAFT HAD AN INFLIGHT ENGINE CHIP LIGHT.  PILOT LANDED AS SOON AS POSSIBLE.  AIRCRAFT WAS LANDED UNDER ITS OWN POWER (NORMAL LANDING).  PILOT THEN SHUT THE AIRCRAFT DOWN TO CHECK ALL ENGINE CHIP DETECTORS.  HE FOUND METAL ON THE ELECTRIC CHIP PLUG, ENGINE OIL TANK CHIP PLUG AND THE ENGINE MOI CHIP PLUG. ENGINE WAS REMOVED AND SENT TO MFG.  ANOTHER ENGINE WAS INSTALLED. (TC NR 20061218004)                                                                                                                                                                                                                                                                                                                                1G71 3U3  U  H9EU    E00054EN             
20070125002552007012500255CE  2007       1          25         CA061218005      120060724G3110903640143       CIRCUIT BOARD                           BEECH 100   A100        1152915CE  PWA   PT6   PT6A28           EA  HARTZLHCB4T HCB4TN3     GL  ANNUNCIATOR PANEMALFUNCTIONED   W      K   NONE                                                                                            N  FALSE WARNING                                                                 ININSP/MAINT     1                      CA                                                                      (CAN) ANNUNCIATOR PANEL SHOWED A FALSE WARNING INDICATION FOR MASTER CAUTION LIGHT.  SYSTEM TROUBLESHOOTING CARRIED OUT AND FOUND FAULT WARNING CIRCUIT BOARD UNSERVICEABLE AND FAULT WARNING CIRCUIT BOARD REPLACED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L72 3T4  T  A14CE   E4EA    6  CP40EA    
20070125002652007012500265GL  2007       1          25         CA061218006      220061205G7310                DRAIN MAST                              LKHEED382   382G        526414USO  ALLSN 501D  501D22A     03006GL  HAMSTD54H   54H60117    NE  NR 2 ENGINE     LEAKING         W      E   ENGINE SHUTDOWN                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CLCLIMB          1                      CA                                                                      (CAN) ENROUTE AFTER MISSED APPROACH AT SNAP LAKE THE CREW OBSERVED A FUEL LEAK AT THE DRAIN MAST ON NR 2 ENGINE.  THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT CONTINUED TO DESTINATION WITHOUT FURTHER PROBLEM. MAINTENANCE DETERMINED THE LEAK SOURCE TO BE FROM THE MANIFOLD DRAIN COLLECTOR. THE MANIFOLD WAS CAPPED AND THE AIRCRAFT COMPLETED A SATIFACTORY GROUND RUN BEFORE RETURN TO SERVICE. (TC NR 20061218006)                                                                                                                                                                                                                                                                                                                          2H74 4T4  T  A1SO    E282    6  CP906     
20070507001112007050700111NE  2007       5          7          CA061218007      120061202G7931                OIL SYSTEM                              SKRSKYS64   S64E        8142604NE  PWA   JFTD12JFTD12A4A   52047NE                              ENGINE          MALFUNCTIONED   W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            DEDESCENT        1                      CA                                          638214                      (CAN) THE AIRCRAFT WAS INVOLVED IN HELICOPTER LOGGING OPERATIONS.  AS THE AIRCRAFT WAS APPROACHING THE LOG LANDING WITH A LOAD, THE FLIGHT CREW WERE ALERTED BY A LOW OIL PRESSURE WARNING LIGHT FOR THE NR (2) ENGINE. A SCAN OF THE CORRESPONDING OIL PRESSURE INDICATOR CONFIRMED THE ENGINE OIL PRESSURE HAD DROPPED TO 20 PSI. AS THE PILOT RELEASED THE LOAD OF LOGS ON THE LOG LANDING THE OIL PRESSURE RETURNED TO NORMAL. THE FLIGHT CREW ELECTED TO RETURN TO THE SERVICE LANDING TO HAVE THE MAINT PERSONNEL INVESTIGATE THE PROBLEM. ENROUTE THE LOW OIL PRESSURE LIGHT ILLUMINATED AGAIN WITH THE CORRESPONDING OIL PRESSURE INDICATION DROPPING TO 20 PSI. AT THIS TIME THE FLIGHT CREW ELECTED TO SHUTDOWN THE NR (2) ENGINE AS A2G72 4U4  U  H4EA    E15EA                
20070125002662007012500266EA  2007       1          25         CA061218008      220061216G853005K21108        SLEEVE                                  PIPER PA31  PA31350     7103110SO  LYC   O540  TIO540J2BD  41532EA  HARTZLHCE3Y HCE3YR2A    GL  CYLINDER        DAMAGED         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA            930                           RL90768A                    (CAN) DURING INSPECTION OIL WAS NOTED ON THE BOTTOM COWL OF ENGINE. UPON CLOSER INSPECTION,  NR 4 CYLINDER WAS FOUND TO BE WET AT THE CYLINDER TO HEAD FLANGE. AFTER CLEANING, OIL WAS SEEN TO BE SEEPING FROM FLANGE AREA. THERE WAS NO VISIBLE CRACK SO DYE PENETRANT WAS CARRIED OUT, AT THIS TIME A PINHOLE WAS REVEALED. COMPRESSION WAS GOOD DURING THE INSPECTION, THE JUG WAS CHANGED OUT FOR A NEW ONE. (TC NR 20061218008)                                                                                                                                                                                                                                                                                                            1L72 3O3  O  A20SO   E14EA   5  CP33EA    
20070507001122007050700112CE  2007       5          7          CA061218009      120061215G55201156100103      TORQUE TUBE                             BEECH 100   B100        1152919CE  GARRTTTPE331TPE3316252B 01514WP  HARTZLHCB4T HCB4TN5     GL  ELEVATOR        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            958                                                       (CAN) DURING COMPLIANCE WITH SB 2145, CHANGED OUT THE DUE TORQUE TUBES AND REPLACE THEM WITH INSPECTED ONES. WHEN THE LT WAS REMOVED A CRACK WAS NOTED GOING FROM THE TAPER PIN HOLE TO THE EDGE OF THE TORQUE TUBE MOUNT BRACKET. IT APPEARS THAT THE PIN WAS OVER-TORQUED DURING ASSEMBLY LEADING TO THE CRACK. (TC NR 20061218009)                                                                                                                                                                                                                                                                                                                                                                                                           1L72 4T4  T  A14CE   E2WE    6  CP40EA    
20070507001922007050700192NE  2007       5          7          CA061218010      120061121G5302NAS146A37       BOLT                                    SKRSKYS64   S64E        8142604NE  PWA   JFTD12JFTD12A4A   52047NE                              TAIL BOOM       DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) THE AIRCRAFT WAS INVOLVED IN HELICOPTER LOGGING OPERATIONS.  THE YARDING PROFILE WAS A DOWN HILL FLIGHT FROM THE HARVEST CUT BLOCK TO A ROAD SIDE LOG LANDING. AFTER ENCOUNTERING DOWN FLOWING WIND CONDITIONS THROUGH OUT THE FIRST LOGGING CYCLE OF THE DAY THE FLIGHT CREW ELECTED TO SHUTDOWN AND WAIT FOR MORE FAVORABLE WIND CONDITIONS.  DURING A ROUTINE POST FLIGHT INSPECTION OF THE AIRCRAFT, THE MAINTENANCE PERSONNEL WERE CHECKING THE HORIZONTAL STABILIZER FOR GENERAL CONDITION AND SECURITY WHEN THEY DISCOVERED IT TO BE LOOSE. FURTHER INSPECTION OF THE STABILIZER TO PYLON FORWARD ATTACHMENT FITTINGS REVEALED THE BOLT THAT ATTACHES THE (2) FITTINGS WAS MISSING. A VISUAL INSPECTION OF THE ENTIRE AIRCRAFT UNCO2G72 4U4  U  H4EA    E15EA                
20070507001132007050700113CE  2007       5          7          CA061218011      120061215G55201156100103      TORQUE TUBE                             BEECH 100   B100        1152919CE  GARRTTTPE331TPE3316252B 01514WP  HARTZLHCB4T HCB4TN5     GL  ELEVATOR        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            988                                                       (CAN) DURING COMPLIANCE WITH SB 2145 (REMOVED THE DUE TUBES TO SEND OUT FOR NDT AND REPLACE WITH INSPECTED SERVICEABLE ONES), A CRACK WAS DISCOVERED RADIATING FROM ONE OF THE TAPER PIN HOLES TO THE EDGE OF THE ATTACH BOSS ON THE LT TUBE. IT APPEARS THAT THE TAPER PIN WAS OVERTORQUED DURING ASSEMBLY CAUSING THE CRACK. THE TUBE HAS BEEN SCRAPPED. (TC NR 20061218011)                                                                                                                                                                                                                                                                                                                                                                  1L72 4T4  T  A14CE   E2WE    6  CP40EA    
20070125002932007012500293NE  2007       1          25         CA061218012      220061215G7261                OIL SYSTEM                              PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  ENGINE          CONTAMINATED    W      A   UNSCHED LANDING                                                                                 CJ F.O.D.                    WARNING INDICATION                                  NRNOT REPORTED   1                      CA       8331 215                                                       (CAN) NON ALLOWABLE DEBRIS FOUND IN OIL SYSTEM, CONFIRMED BY OIL ANALYSIS REPORT. ENGINE SENT BACK TO MANUFACTURER FOR INVESTIGATION. ENGINE EXCHANGED, WILL NOT BE SENT BACK TO THE OPERATOR. ENGINE TSO 214.7 TSN 8330.9 (TC NR 20061218012)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20070125002942007012500294NM  2007       1          25         CA061218013      120061129G3260H1010153        SWITCH                                  BOEING727   727223      1384074NM  PWA   JT8   JT8D15A     52051NE                              MLG             MALFUNCTIONED   W      O   OTHER                                                                                           N  FALSE WARNING                                                                 APAPPROACH       1                      CA                                                                      (CAN) NOSE GEAR GREEN LIGHT DID NOT ILLUMINATE WITH LANDING GEAR SELECTED DOWN.  VISUALLY INSPECTED TO ENSURE NOSE GEAR WAS DOWN AND LOCKED THROUGH VIEWPORT AND CONFORMED NOSE GEAR WAS DOWN AND LOCKED.  AS A PRECAUTIONARY ACTION NOSE GEAR LOCK SWITCH REMOVED AND REPLACED ALONG WITH CONNECTOR D298 IAW MM 32-61-71. FUNCTION CHECKED SERVICEABLE. NO FURTHER OCCURRENCE REPORTED. (TC NR 20061218013)                                                                                                                                                                                                                                                                                                                                    2L73 4F4  F  A3WE    E2EA                 
20070125002952007012500295GL  2007       1          25         CA061218014      320061218G6111A163395         SEAL                                    CESSNA206   TU206G      2073357CE  CONT  O520  TSIO520M    17040SO  MCAULYD3A34 D3A34C402   GL  PROPELLER       LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA            226   810380                              810380          (CAN) BLADE GREASE SEAL FAILED. GREASE LEAVING HUB. PROP REMOVED AND SENT TO REPAIR FACILITY WHERE NEW SEALS WERE INSTALLED. PROP REINSTALLED AND A/C SERVICEABLE (TC NR 20061218014).                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3O3  O  A4CE    E8CE    5  CP47GL    
20070125002962007012500296EA  2007       1          25         CA061218015      120061218G2913                PUMP                                    CNDAIRCL601 CL6013A     8070802EA  GE    CF34  CF343A      30015NE                              HYDRAULIC  SYS  DAMAGED         W      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA       1371       2353858                                             (CAN) LOST OF NR 3 SYSTEM HYDRAULIC FLUID IN FLIGHT. THE NR 3B PUMP HAS FAILED ON FLANGE GASKET.  THE PUMP HAS BEEN REPLACED AND A\C RETURNED TO SERVICE. A/C HOURS:  6816:27 A/C CYCLES ; 7302  (TC NR 20061218015)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F4  FRTA21EA   E15NE                
20070507001142007050700114SW  2007       5          7          CA061218016      120061108G291070060T000X186   HOSE                                    BELL  427   427         1182207SW                                                               HYD SYSTEM      CHAFED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) HOSE ASSEMBLY 70-060T000X186 (18.750 INCHES LONG) RUBS AGAINST SUPPORT 427-001-005 WHEN THE COLLECTIVE STICK IS DOWN AND THE CYCLIC STICK IS  CENTER AND FULL FORWARD. (TC NR 20061218016)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1G71 3U      R00001RC                     
20070125002972007012500297EA  2007       1          25         CA061218017      120061117G76032100140003      GEARBOX                                 CNDAIRCL600 CL6002B16   1900305EA  GE    CF34  CF343A1     30015NE                              THROTTLE        STIFF           W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             LDLANDING        1                      CA       4134                                                           (CAN) PILOT REPORTED LT POWER LEVER STIFF TO MOVE AS COMPARED TO RT. TROUBLESHOOTING REVEALED THAT INPUT SHAFT ON GEARBOX ATTACHED, (COULD BARELY BE RETACTED BY HAND).  SB601-0583 (TC NR 20061218017)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRTA21EA   E15NE                
20070125002982007012500298NM  2007       1          25         CA061218018      120061218G271082740191053     ROD                                     DHAV  DHC8  DHC8102     2809003NM                                                               AILERON         MISINSTALLED    W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA                                                                      (CAN) DURING C-CHECK, A INSPECTOR FOUND THE AILERON INPUT ROD NOT PROPERLY INSTALLED ON BOTH SIDE LT AND RT AILERON.  THE ROD END WAS FABRICATED WITH A CUT OUT FOR AVOID THE CONTACT BETWEEN THE ROD END AND THE QUADRANT SHAFT.  ON THE SAME A/C, WE FOUND THE BOTH ROD DIRECTLY IN CONTACT WITH THE SHAFT IN FULL TRAVEL POSITION.  ATTACH 2 VERY CLEAR PICTURES WITH THIS FDR. (TC NR 20061218018)                                                                                                                                                                                                                                                                                                                                          2H72 4T    RTA13NM                        
20070125002992007012500299    2007       1          25         CA061218019      420061218G611305503214        BULKHEAD                                CESSNA172   172N        2072434CE  LYC   O320  O320D2J     41508EA  MCAULY1C160 1C160DTM    GL  SPINNER         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       50                                                             (CAN) THIS AIRCRAFT HAS HAD ALL THE AFT BULKHEAD AND HEAVIER SPINNER UPGRADES AND HAS HAD IT ALL ASSEMBLED IAW THE LATEST SB.  THE (FORWARD SPINNER BULKHEAD) IS CRACKED AGAIN WITH LESS THEN 50 HOURS TSN, CRACKS RADIATING .2500 TO 1 INCH FROM 3 OF THE 6 HOLES.   YOU HAVE TO LOOK VERY CARFULLY AS THE CRACKS RADIATING FROM THE PROP BOLT HOLES ARE VERY FINE AND HIDE UNDER THE FACTORY PRIMER. (TC NR 20061218019)                                                                                                                                                                                                                                                                                                                      1H71 3O3  ONT3A12    E274    5  NP910     
20070125003002007012500300EA  2007       1          25         CA061218020      120061124G61238190026         PRESSURE SWITCH                         DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A27      52043EA  HARTZLHCB3T HCB3TN3     GL  AUTOFEATHER     FAILED          W      K   NONE                                                                                            L  NO TEST                                                                       ININSP/MAINT     1                      CA                                                                      (CAN) ON INVESTIGATION OF THE REPORTED AUTOFEATHER DEFECT, THE LT ENGINE PRESSURE SWITCH, PN 8190026, WAS FOUND TO BE DEFECTIVE. REPLACEMENT OF THE COMPONENT CURED THE PROBLEM WHICH IS CONSIDERED TO BE AN ISOLATED RANDOM FAILURE. (TC NR 20061218020)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H72 3T4  TRTA9EA    E4EA    6  CP15EA    
20070125003212007012500321NM  2007       1          25         CA061219001      120061126G7500655881313       DUCT                                    BOEING727   727225      1384077NM  PWA   JT8   JT8D15A     52051NE                              BLEED AIR SUPPLYDISCONNECTED    W      O   OTHER                                                                                           J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) LOWER AFT BODY HEAT WARNING LIGHT ILLUMINATED IN FLIGHT. FLIGHT CREW FOLLOWED EMERGENCY CHECKLIST AND LIGHT EXTINGUISHED WHEN NR 3 BLEED AND THRUST LEVER CLOSED.  UPON INVESTIGATION MAINTENANCE DISCOVERED SUPPLY DUCT FORWARD OF STA 1183 DISCONNECTED AND DUCT DAMAGED. DUCT AND CLAMPS REPLACED, ENGINE RUNS AND LEAK CHECKS CARRIED OUT. NO FURTHER PROBLEMS NOTED. (TC NR 20061219001)                                                                                                                                                                                                                                                                                                                                             2L73 4F4  F  A3WE    E2EA                 
20070125003222007012500322NM  2007       1          25         CA061219002      120061116G561058935733        WINDOW                                  BOEING727   727223      1384074NM  PWA   JT8   JT8D15A     52051NE                              COCKPIT         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING SERVICING THE L4 WINDOW WAS FOUND CRACKED.  WINDOW REPLACED IAW MM 56-11-31, FUNCTION CHECKED SERVICEABLE WITH NO FURTHER FAULTS REPORTED. (TC NR 20061219002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L73 4F4  F  A3WE    E2EA                 
20070125003242007012500324NM  2007       1          25         CA061219003      120061122G3242                DISC                                    BOEING727   727223      1384074NM  PWA   JT8   JT8D15      52051NE                              BRAKE ASSY      DETACHED        W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA                  A0726                                               (CAN) WHILE TOWING AIRCRAFT TO LINE IT WAS REPORTED THAT NR 1 BRAKE WAS TRYING TO LOCK UP. UPON REMOVAL OF BRAKE ASSEMBLY THE DISC RING WAS FOUND DETACHED FROM THE ASSEMBLY. A RIVET WAS FOUND SHEARED AND THE DISC RING CAME APART.  FURTHER TO FOLLOW AFTER STRIP REPORT IS RECEIVED FROM OVERHAUL FACILITY. (TC NR 20061219003)                                                                                                                                                                                                                                                                                                                                                                                                             2L73 4F4  F  A3WE    E2EA                 
20070507001152007050700115GL  2007       5          7          CA061219004      220061121G732323036657        GOVERNOR                                BELL  206   206L        1181522SW  ALLSN 25OC  250C20R          GL                              ENGINE          ERRATIC         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            1889                                                      (CAN) HIGH TIME GOVERNOR TSO 1889.2, REMOVED FOR O/H DUE TO ERRATIC RPM   REPLACED WITH NEW GOVERNOR PN 23076061 SN HR47346 TSN 0:0 (TC NR 20061219004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1G71 3U3  U  H2SW    E4CE                 
20070507001162007050700116GL  2007       5          7          CA061219005      220061121G7323718513          ACTUATOR                                BELL  206   206L        1181522SW  ALLSN 25OC  250C20R          GL                              ENGINE          FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) REMOVED LINEAR ACTUATOR PN 7185-13 SN 0296A DUE TO INTERNAL LOCKING CLIP FALLING OFF. INSTALLED SERVICEABLE USED LINEAR ACTUATOR PN 206-062-721-003 SN 11842. (TC NR 20061219005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1G71 3U3  U  H2SW    E4CE                 
20070507001172007050700117SO  2007       5          7          CA061219006      120060123G2497KA39            CONVERTER                               PIPER PA31  PA31350     7103110SO                                                               NR 1 NAV COMM   MALFUNCTIONED   W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) VOLTAGE CONVERTER SUPPLYING POWER TO NR 1 NAV COM FAILED CAUSING LOSS OF POWER TO RADIO (TC NR 20061219006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L72 3O      A20SO                        
20070507001182007050700118CE  2007       5          7          CA061219007      120061106G24971385            RELAY                                   BEECH 100   A100        1152915CE  PWA   PT6   PT6A28           EA  HARTZLHCB4T HCB4TN3     GL  OVERVOLTAGE     FAILED          W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) AFTER TAKEOFF ON CLIMB-OUT THE RT GENERATOR CHARGING SYSTEM FAILED. THE AIRCRAFT RETURNED TO BASE. SYSTEM TROUBLESHOOTING CARRIED OUT AND FOUND THE OVER VOLTAGE RELAY HAD FAILED. (TC NR 20061219007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L72 3T4  T  A14CE   E4EA    6  CP40EA    
20070125003262007012500326CE  2007       1          25         CA061219009      120060913G8010S1991A1         RELAY                                   CESSNA150   150M        2071830CE  CONT  O200  O200A       17020SO  MCAULY1A102 1A102OCM    GL  STARTER         STUCK           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) POWER ON STARTER WITH WHEN MASTER SWITCH ON.  FOUND MASTER RELAY STUCK IN POSITION. NEW RELAY S-1991-A1 INSTALLED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1H71 3O3  O  3A19    E252    5  NP918     
20070125003272007012500327SW  2007       1          25         CA061219010      120061215G80113108281         INSERT                                  SWRNGNSA227 SA227AC     8780603SW  GARRTTTPE331TPE33111U   01514WP  MCAULY4HFR344HFR34C652  NE  STARTER         WORN            W      K   NONE                                                                                            J  WARNING INDICATION                                                            ININSP/MAINT     1                      CA                                                                      (CAN) UPON START PROP STARTED TO ROTATE AND THEN STOPPED.  STARTER CONTINUED TO TURN.  TORLON INSERT WAS WORN ENOUGH THAT THE STARTER TURNED INSIDE THE TORLON INSERT.  INSERT WAS REPLACED AND AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20061219010)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4T4  TRTA8SW    E4WE    6  C3PNE     
20070125003282007012500328NE  2007       1          25         CA061219011      220061107G7530                LINE                                    AEROSPATR42 ATR42*      8680900EU  PWA   120   PW120            NE                              P3              FRACTURED       W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) DURING A MAINTENANCE TEST FLIGHT A LOUD NOISE WAS HEARD ACCOMPANIED BY AN ENGINE FIRE WARNING.  THE ENGINE WAS SHUTDOWN IN FLIGHT AND FIRE BOTTLES DISCHARGED.  SUBSEQUENT INSPECTION REVEALED A FRACTURED ENGINE P3 BLEED AIR TUBE. (TC NR 20061219011)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2H72 4T4  TRTA53EU   E20NE                
20070125003292007012500329NE  2007       1          25         CA061219012      220061022G7200                ENGINE                                  CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE                                              UNKNOWN         W      O   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      CA                                                                      (CAN) IN FLIGHT A LOUD NOISE WAS HEARD AND THE WINDSHIELD BECAME COVERED IN OIL.  A FORCED LANDING FOLLOWED RESULTING IN AIRFRAME DAMAGE.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3T3  T  A37CE   E4EA                 
20070125003302007012500330EA  2007       1          25         CA061219013      220061103G75303035279         TUBE                                    DHAV  DHC7  DHC7103     2802710EA  PWA   PT6   PT6A50      52043EA  HAMSTD24PF  24PF305     GL  FCU             FRACTURED       W      E   ENGINE SHUTDOWN                                                                                 R  PARTIAL RPM/PWR LOSS                                                          CLCLIMB          1                      CA                                                                      (CAN) ENGINE POWER ROLLED BACK UNCOMMANDED DURING CLIMB.  THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED A FRACTURED P3 PRESSURE LINE TO THE FUEL CONTROL UNIT. (TC NR 20061219013)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2H74 4T4  T  A20EA   E4EA    6  CP1NE     
20070125003312007012500331    2007       1          25         CA061219014      320061109G6110                SEAL                                    BAG   ATP   ATP                EU  PWA   PW120 PW126A           NE                              PROPELLER SHAFT LEAKING         W      E   ENGINE SHUTDOWN                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) DURING CRUISE, THE ENGINE OIL PRESSURE BEGAN TO FLUCTUATE IN THE RED BAND.  THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT RETURNED TO POINT OF DEPARTURE. SUBSEQUENT INSPECTION REVEALED A LEAK AT THE PROP SHAFT OIL SEAL.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061219014)                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4T4  TRTA27NM   E2ONE                
20070125003362007012500336EA  2007       1          25         CA061219015      220061101G7200                ENGINE                                  EMB   110   EMB110*            SO  PWA   PT6   PT6A34      52043EA                                              DAMAGED         W      E   ENGINE SHUTDOWN                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  DEDESCENT        1                      CA                                                                      (CAN) ON TAKEOFF, ENGINE OIL PRESSURE WAS SEEN TO FLUCTUATE.  THE FIGHT CONTINUED AND ON DESCENT ENGINE OIL PRESSURE FELL TO ZERO RESULTING IN A PROPELLER AUTOFEATHER.  THE ENGINE WAS SHUTDOWN IN FLIGHT.  GROUND INSPECTION REVEALED INTERNAL ENGINE DAMAGE.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                      1L72 4T4  TRTA21SO   E4EA                 
20070125003382007012500338CE  2007       1          25         CA061219016      120061116G7312311705601       HEATER                                  BEECH MU300 400BEECH           CE  PWA   JT15  JT15D5      52112NE                              FUEL            LEAKING         W      E   ENGINE SHUTDOWN                                                                                 KRJFLUID LOSS                PARTIAL RPM/PWR LOSS      WARNING INDICATION        CRCRUISE         1                      CA                                                                      (CAN) DURING FLIGHT ENGINE FUEL PRESSURE BEGAN TO FLUCTUATE FOLLOWED BY AN UNCOMMANDED POWER REDUCTION.  THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20061219016)                                                                                                                                                                                                                                                                                                                                                                                                                                                       2H72 4F4  FRTA16SW   E25EA                
20070125003402007012500340NE  2007       1          25         CA061219017      220061115G7310                MANIFOLD                                CESSNA560   560XL       2076702CE  PWA   545   PW545A           NE                              FUEL SYSTEM     LEAKING         W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         AKJFLAME/FIRE                FLUID LOSS                WARNING INDICATION        DEDESCENT        1                      CA                                                                      (CAN) ON DESCENT THE ENGINE FIRE WARNING ACTIVATED AND THE ENGINE WAS SHUTDOWN IN FLIGHT.  POST FLIGHT INSPECTION REVEALED LEAKAGE FROM THE ENGINE FUEL MANIFOLD AND EVIDENCE OF BURNING OF THE ENGINE INNER BYPASS DUCTING. (TC NR 20061219017)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F4  FRTA22CE   E00059EN             
20070125003442007012500344EA  2007       1          25         CA061219020      220061115G7200                ENGINE                                  DHAV  DHC6  DHC6200     2802620EA  PWA   PT6   PT6A27      52043EA                                              FAILED          W      D   RETURN TO BLOCK                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA                                          24085                       (CAN) DURING TAXI, THE ENGINE EMITTED A NOISE AND LOST POWER.  SUBSEQUENT INSPECTION REVEALED INTERNAL ENGINE DAMAGE.  MFG WILL INVESTIGATE AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H72 3T4  TRTA9EA    E4EA                 
20070125003662007012500366NE  2007       1          25         CA061219021      220061120G7261JT5D5           ENGINE                                  BEECH MU300 400BEECH           CE  PWA   JT15  JT15D5      52112NE                                              MALFUNCTIONED   W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            DEDESCENT        1                      CA                  100119                  100119                      (CAN) THE ENGINE OIL FILTER BYPASS INDICATOR ACTIVATED IN DESCENT AND THE ENGINE WAS SHUTDOWN IN FLIGHT.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2H72 4F4  FRTA16SW   E25EA                
20070125003672007012500367EA  2007       1          25         CA061219022      220060925G7261PT6A64          ENGINE                                  SOCATATBM   TBM700      8682000EU  PWA   PT6   PT6A64           EA                                              LEAKING         W      E   ENGINE SHUTDOWN                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA                                          111106                      (CAN) IN FLIGHT THE ENGINE OIL TEMPERATURE INCREASED ACCOMPANIED BY A LOSS OF OIL PRESSURE.  THE ENGINE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED METAL CONTAMINATION OF THE OIL SYSTEM, INTERNAL OIL LEAKAGE AND SEIZURE OF THE REDUCTION GEAR BOX.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED.                                                                                                                                                                                                                                                                                                                                                                                                    1L71 3T4  TRTA60EU   E4EA                 
20070125003682007012500368EU  2007       1          25         CA061219023      120061123G7712                ENGINE                                  FOKKERF27   F27MK50            EU  PWA   PWA120PW125B           NE                                              MALFUNCTIONED   W      E   ENGINE SHUTDOWN                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) IN CRUISE THE ENGINE EXPERIENCED TORQUE FLUCTUATIONS ACCOMPANIED BY INCREASED ITT TEMPERATURES.  THE ENGINE WAS SHUTDOWN IN FLIGHT AND THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  MFG WILL MONITOR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061219023)                                                                                                                                                                                                                                                                                                                                                                                                                                           2H72 4T4  TRTA817    E20NE                
20070125003692007012500369NE  2007       1          25         CA061219024      220061126G7250                TURBINE BLADES                          AEROSPATR42 ATR42500    8680948EU  PWA   PW120 PW127            NE                              ENGINE          DAMAGED         W      EC  ENGINE SHUTDOWN         ABORTED TAKEOFF                                                         J  WARNING INDICATION                                                            TOTAKEOFF        1                      CA                                                                      (CAN) ON TAKE-OFF, THE ENGINE FIRE WARNING ACTIVATED AND THE CREW SHUT THE ENGINE DOWN IN FLIGHT AND DISCHARGED THE FIRE BOTTLES.  THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED DAMAGED POWER TURBINE BLADES AND METAL IN THE ENGINE OIL.  MFG WILL INVESTIGATE THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED. (TC NR 20061219024)                                                                                                                                                                                                                                                                                                                                                                         2H72 4T4  TRTA53EU   E20NE                
20070125003702007012500370SW  2007       1          25         CA061219025      120061120G56102719442003      WINDSHIELD                              SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP                              COCKPIT         FAILED          W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      CA       3868                                                           (CAN) DURING FLIGHT THE LT COCKPIT HEATED WINDSHEILD SHATTERED BUT REMAINED INTACT. THE AIRCRAFT IMMEDIATLY RETURNED TO THE AIRPORT AND THE WINDOW WAS REPLACED BY MAINTENANCE.  NO CAUSE COULD BE DETERMINED AS TO WHY THIS WINDOW SHATTERED. (TC NR 20061219025)                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4T4  TRTA8SW    E4WE                 
20070125003712007012500371EA  2007       1          25         CA061219026      220061128G7250                TURBINE BLADES                          BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA                              ENGINE          FAILED          W      O   OTHER                                                                                           XJ ENGINE FLAMEOUT           WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) IN CRUISE THE ENGINE EMITTED A LOUD NOISE AND FLAMED OUT.  SUBSEQUENT INSPECTION REVEALED FRACTURED TURBINE BLADES AND VANES AND A PUNCTURED GAS GENERATOR CASE.  LIGHT IMPACT DAMAGE WAS FOUND ON THE AIRCRAFT WING LEADING EDGE AND FUSELAGE WINDOWS.  MFG WILL INVESTIGATE THE EVENT AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061219026)                                                                                                                                                                                                                                                                                                                                                                               1L72 4T4  T  A24CE   E4EA                 
20070125003722007012500372SW  2007       1          25         CA061219027      120061215G56102719442004      WINDSHIELD                              SWRNGNSA226 SA226TC     8780404SW  GARRTTTPE331TPE33110UA  01514WP                              COCKPIT         FAILED          W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      CA       1299                                                           (CAN) DURING FLIGHT THE RT COCKPIT HEATED WINDSHEILD SHATTERED BUT REMAINED INTACT. THE FLIGHT CREW DECALRED AN EMERGENCY AND RETURNED TO THE AIRPORT UNEVENTFULLY. THE WINDOW WAS REPLACED BY MAINTENANCE. THE CREW EXPLAINED THAT PRIOR TO THE WINDOW SHATTERING A ELECTRICAL DISCHARGE WAS WITNESSED GOING ACROSS THE WINDSHIELD. OTHER THAN THE STATIC DISCHARGE, NO CAUSE FOR THE WINDOW TO SHATTER HAS BEEN DETERMINED. (TC NR 20061219027)                                                                                                                                                                                                                                                                                               2L72 4T4  TRTA8SW    E4WE                 
20070125003732007012500373NM  2007       1          25         CA061219028      120061213G52306557204520      ROD                                     BOEING727   727227      1384078NM  PWA   JT8   JT8D9A      52048NE                              CARGO DOOR      BENT            W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         O  OTHER                                                                         CLCLIMB          1                      CA                                                                      (CAN) ON ROTATION, NR 2 CARGO DOOR LIGHT ILLUMINATED.  NR 3 ENGINE SURGED AND A SHUTDOWN PROCEDURE WAS CARRIED OUT. THE A/C LANDED SAFELY, WHERE A LEVEL 1 BORESCOPE INSPECTION WAS CARRIED OUT, WITH NO FOD DAMAGE FOUND. UPON INSPECTION, THE CARGO DOOR WAS FOUND TO BE OPEN BUT IN THE LATCHED POSITION. THE CARGO DOOR WOULD NOT CLOSE. FURTHER INSPECTION FOUND 4 BENT DOOR HINGE ROD ARMS. THE NR 2 CARGO DOOR, HINGE ARMS AND POSITIONING SWITCH WERE REPLACED. THE ASSEMBLY FUNCTIONED PROPERLY AND THE A/C WAS RETURNED TO SERVICE.   (TC NR 20061219028)                                                                                                                                                                             2L73 4F4  F  A3WE    E2EA                 
20070129003452007012900345EU  2007       1          29         CA061219029      220061210G7310                FUEL                                    BRAERO748   HS7482A     4231001EU  RROYCEDART  DART5342         EU  ROTOL R4304 R2124304    EU  FUEL SYSTEM     CONTAMINATED    W      A   UNSCHED LANDING                                                                                 XJ ENGINE FLAMEOUT           WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) PILOT OBSERVED ENGINE NR 1 FUEL FILTER DE-ICING WARNING LIGHT ILLUMINATED IN CRUISE FLIGHT. SHORTLY AFTER APPLYING FUEL HEAT, ENGINE NR 1 QUIT.  PILOT FEATHERED PROPELLER AND LANDED UNEVENTFUL. MAINT REMOVED ENGINE NR 1 LOW PRESSURE FUEL FILTER AND FOUND A LACK OF FUEL. MAINT THEN DRAINED CONTENTS OF NR 1 FUEL COLLECTOR TANK INTO A BUCKET AND OBSERVED .5 LITER OF WATER PRESENT IN FUEL. MAINT FILLED AND DRAINED TANK 3 MORE TIMES TO ENSURE ALL WATER CONTAMINATION HAD BEEN REMOVED. NR 1 ENGINE FUEL SYS WAS RESTORED IAW MM. ENGINE WAS RUN AND TESTED SERVICEABLE. MAINT CHECKED FOR WATER CONTAMINATION IN THE LT WING SUMP, RT WING SUMP AND NR 2 FUEL COLLECTOR TANK AND FOUND NO EVIDENCE OF WATER. OPERATOR CHECKED2L72 3T4  T  A24EU   A196    6  CP899     
20070125003742007012500374SW  2007       1          25         CA061220001      120061220G275021903           CABLE                                   BBAVIA8     8GCBC       1220803SW                                                               FLAP HANDLE ASSYFRAYED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) CABLE FOUND FRAYED AT FWD END WHERE CABLE BENDS HARD OFF OF HANDLE TRACK TO FWD CABLE ATTACH POINT. (TC NR 20061220001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3O      A21CE                        
20070125003752007012500375NM  2007       1          25         CA061220002      120061127G793130C2083         TRANSDUCER                              AMD   FALC50FALCON2000  2730170NM                                                               OIL PRESS TRANSDUNSERVICEABLE   W      E   ENGINE SHUTDOWN                                                                                 N  FALSE WARNING                                                                 NRNOT REPORTED   1                      CA                                                                      (CAN) ENGINE OIL PRESSURE INDICATION FLUCTUATED IN FLIGHT AND FELL BELOW 35 PSI.  AS A PRECAUTION, THE ENGINE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INVESTIGATION REVEALED A FAULTY MAIN OIL PRESSURE TRANSDUCER. (TC NR 20061220002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2K72 4F    RTA50NM                        
20070125003802007012500380EA  2007       1          25         CA061220003      220061022G7230                TURBINE BLADES                          DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A27      52043EA                              ENGINE          DAMAGED         W      E   ENGINE SHUTDOWN                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CRCRUISE         1                      CA                                          41691                       (CAN) DURING CRUISE THE ENGINE EMITTED A LOUD NOISE ACCOMPANIED BY A DECAY ON ENGINE PARAMETERS.  THE ENGINE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED DAMAGE TO COMPRESSOR AND POWER TURBINE BLADES.  MFG WILL MONITOR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE DETERMINED.                                                                                                                                                                                                                                                                                                                                                                                                                                      1H72 3T4  TRTA9EA    E4EA                 
20070125003822007012500382EA  2007       1          25         CA061220004      220061128G7200                ENGINE                                  BEECH 1900  1900C       1154161CE  PWA   PT6   PT6A65B     52043EA                                              MALFUNCTIONED   W      CE  ABORTED TAKEOFF         ENGINE SHUTDOWN                                                         E  VIBRATION/BUFFET                                                              TOTAKEOFF        1                      CA                                          32399                       (CAN) THE ENGINE EMITTED A LOUD NOISE ON TAKE-OFF ROLL.  TAKE-OFF WAS ABORTED AND THE ENGINE SHUTDOWN.  MFG WILL MONITOR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20061220004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4T4  TRTA24CE   E4EA                 
20070125003832007012500383NE  2007       1          25         CA061220005      220061010G7210                BOLT                                    BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE                              1ST STAGE CARRIESHEARED         W      E   ENGINE SHUTDOWN                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) IN CRUISE FLIGHT, ENGINE OIL PRESSURE WAS SEEN TO FLUCTUATE AND THEN DECAY TO ZERO.  THE ENGINE WAS SHUTDOWN IN  FLIGHT.  SUBSEQUENT INVESTIGATION REVEALED A SHEARED 1ST STAGE REDUCTION GEAR BOX CARRIER BOLT. (TC NR 20061220005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4T4  TRTA24CE   E26NE                
20070125003842007012500384CE  2007       1          25         CA061220006      120061214G284066082813        INDICATOR                               CESSNA560   560XL       2076702CE  PWA   545   PW545A           NE                              FUEL SYSS       CHAFED          W      O   OTHER                                                                                           WJ INADEQUATE Q C            WARNING INDICATION                                  DEDESCENT        1                      CA       4429 4429                                                      (CAN) LT FUEL QUANTITY CAUTION LIGHT ILLUMINATES DURING DESCENT. FAULT CODE INDICATES PROBES NR 3 DEFECTIVE.  PROBE NR 3 REPLACED AND FURTHER INVESTIGATION REVEALED THAT THE WIRING IN LT TANK FOUND CHAFING AT (2) PLACES (WS 116.0) ON TOP OF FUEL PILOT VALVE LINE DUE HARNESS ASSEMBLY WAS NOT SUPPORTED PROPERLY DURING THE PRODUCTION ASSEMBLY PROCESS.  NO CHAFING WAS FOUND IN RT FUEL TANK, BUT SIMILAR DEFECTIVE ATTACHMENT WAS FOUND. A SERVICE CONDITION REPORT (SCR NR 268343) WAS DONE TO AIRCRAFT.  (TC NR 20061220006)                                                                                                                                                                                                         2L72 4F4  FRTA22CE   E00059EN             
20070125003852007012500385    2007       1          25         CA061220007      120061218G3246                BEARING                                                                    CFMINTCFM567CFM567B22   13802NE                              MLG WHEEL       FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA       *                                                              (CAN) ON DECEMBER 18, THE CREW REPORTED THAT SOME SLIGHT DRAG WAS FELT IN BRAKING UPON ARRIVAL. INVESTIGATION REVEALED WHAT APPEARS TO BE A NR 4 WHEEL, IB BEARING FAILURE. AN INVESTIGATION INTO THE ROOT CAUSE OF THE FAILURE HAS BEEN INITIATED AND THIS ITEM WILL BE UPDATED ONCE THOSE RESULTS ARE AVAILABLE (TC NR 20061220007)                                                                                                                                                                                                                                                                                                                                                                                                                  4  F          E00055EN             
20070125003862007012500386NM  2007       1          25         CA061220008      120061216G2913623303          PUMP                                    BOEING757   757236      1384971NM  RROYCERB211 RB211535E43754555NE                              HYD SYSTEM      FAILED          W      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  NRNOT REPORTED   1                      CA                  MX607076                                            (CAN) LT ACMP LEAKING FLUID CAUSING LOSS OF HYDRAULIC QUANTITY AND SYSTEM PRESSURE.  AIRCRAFT LANDED AND WAS TOWED OFF THE RUNWAY DUE TO NO NOSE WHEEL STEERING. (TC NR 20061220008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F4  FRTA2NM    E12EU                
20070125003872007012500387WP  2007       1          25         CA061220009      220061219G75302762026311      LINE                                    FRCHLDSA227 SA227DC     3377521SW  GARRTTTPE331TPE33112UHR      WP  MCAULY4HFR344HFR34C652  NE  BLEED AIR       CRACKED         W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB, THE ENGINE FIRE WARNING LIGHT ILLUMINATED. THE ENGINE WAS SHUTDOWN. THE FIRE LIGHT EXTINGUISHED, WHEN THE STOP FEATHER LEVERS WERE PULLED BACK. THE CREW BLEW A FIRE BOTTLE, DECLARED AN EMERGENCY AND LANDED.  A DAMAGED FIRE DETECTOR (1000 DEG F) P/N 17343-61-600 WAS FOUND AND A CRACKED BLEED AIR LINE P/N 27-62026-311  (TC NR 20061220009)                                                                                                                                                                                                                                                                                                                                                                          2L72 4T4  TRTA18SW   E4WE    6  C3PNE     
20070125003882007012500388NM  2007       1          25         CA061221001      120061216G29136617303         PUMP                                    BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  HYD SYSTEM      FAILED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            DEDESCENT        1                      CA       1754                                                           (CAN) DURING DESCENT NR 1 ENG HYD PUMP CAUTION LIGHT ILLUMINATED. CONTINUED TO DESTINATION AIRPORT FOR LANDING WITH OUT INCIDENT. MAINTENANCE CONFIRMED NR 1 ENG DRIVEN PUMP INTERNAL FAILURE.  CASE DRAIN AND PRESSURE FILTERS CONTAMINATED WITH METAL. (TC NR 20061221001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
20070125003892007012500389CE  2007       1          25         CA061221002      120061218G52105043003211      LATCH                                   BEECH 100   A100        1152915CE  PWA   PT6   PT6A28           EA  MCAULY4HFR344HFR34C762  NE  PAX DOOR        BROKEN          W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) DURING FLIGHT THE CREW NOTICED AIR LEAKING OUT THE PASSENGER DOOR AND THE AIRCRAFT BEGAN TO DEPRESSURIZE. THE CREW DESCENDED TO 9000 FT FOR THE REMAINDER OF THE FLIGHT AND LANDED WITHOUT FURTHER INCIDENT. UPON LANDING THEY NOTICED THE LT UPPER DOOR HOOK WAS UNSERVICEABLE. FURTHER INSPECTION BY MAINTENANCE REVEALED THAT THE AFT CABIN DOOR HOOK LATCH BRACKET ATTACHMENT PIN P/N MS20392-2C35 HAD FAILED. THIS FAILURE RENDERED THE DOOR HOOK UNSERVICEABLE. THE DAMAGED WAS NOT LIMITED TO THE CLEVIS PIN IT WAS ALSO FOUND THAT THE MOUNTING BRACKET WAS BENT AND THE BUSHING WAS LOOSE.  THE FRAME, THE BUSHING AND THE PIN WERE REPLACED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20061221002)                           1L72 3T4  T  A14CE   E4EA    6  C3PNE     
20070507001212007050700121CE  2007       5          7          CA061221003      120061218G32301153800025      MOTOR                                   BEECH 200   B200C       1152924CE  PWA   PT6   PT642A           NE  HARTZLHCD4N3HCD4N3A     GL  LANDING GEAR    FAILED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            APAPPROACH       1                      CA                                                                      (CAN) DURING FLIGHT THE LANDING GEAR WOULD NOT EXTEND AND AN EMERGENCY WAS DECLARED. A MANUAL GEAR EXTENSION WAS COMPLETED THE (3) GREEN LIGHTS ILLUMINATED AND THE AIRCRAFT LANDED WITHOUT FURTHER INCIDENT.   MAINTENANCE INVESTIGATED AND FOUND THAT THE LANDING GEAR MOTOR HAD FAILED. THE MOTOR WAS REPLACED, GEAR SWINGS COMPLETED AND THE AIRCRAFT RETURNED TO SERVICE. THIS MOTOR HAS A 2500 LANDING OVERHAUL INTERVAL AND ONLY HAD 390 LSO.  (TC NR 20061221003)                                                                                                                                                                                                                                                                       1L72 4T4  T  A24CE   E4EA    5  CSTC      
20070507001632007050700163    2007       5          7          CA061221004      420061218G2210                AUTOPILOT SYS                           BELL  412   412EP       1182205SW                                                                               MALFUNCTIONED   W      H   DEACTIVATE SYST/CIRCUITS                                                                        F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA                                                                      (CAN) DURING AN APPROACH TO RUNWAY 24 RIGHT AT THE MFG PLANT,  BOTH AUTO-PILOTS WENT OFF LINE. THE MASTER CAUTION LIGHTS WERE OFF ON THE AUTO-PILOTS. A/C WAS ABLE TO LAND. (TC NR 20061221004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1G72 4U      H4SW                         
20070125003902007012500390EA  2007       1          25         CA061221005      120061221G2820AE7010000N130   HOSE                                    CNDAIRCL604 CL604       1900301EA  GE    CF34  CF343B1          NE                              FUEL SYS        RUPTURED        W      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  TXTAXI/GRND HDL  1                      CA       15                                                             (CAN) UPON SHUTDOWN ON THE RAMP, CREW NOTICED A STRONG SMELL OF FUEL WHEN MAIN CABIN DOOR WAS OPENED.  LT MAIN GEAR WAS SITTING IN A PUDDLE OF FUEL.  FOUND ENGINE FUEL FEED AUX TANK LINE RUPTURED.  (IPC 28-21-16 NR 285) (TC NR 20061221005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA21EA   E15NE                
20070125003912007012500391EA  2007       1          25         CA061221006      120061218G2700C6R1806135      CABLE ASSY                              DHAV  DHC6  DHC6        2802606EA  PWA   PT6   PT6A27      52043EA  HARTZLHCB3T HCB3TN3     GL  FLT CONTROLS    INCORRECT       W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA                                                                      (CAN) WHEN AN OPERATOR TRIED TO INSTALL ONE OF THESE CABLE ASSEMBLIES HE FOUND THAT THE END THAT ENGAGES THE SERVO CAPSTAN WOULD NOT FIT PROPERLY SO THAT THE LOCK SCREW COULD BE INSTALLED. UPON INVESTIGATION IT WAS FOUND THAT THE ORIGINAL DRAWING FOR THE CABLE ASSEMBLY PICTORIALLY SHOWED THIS CABLE END SWAGED ON INCORRECTLY. THE DRAWING HAS BEEN CORRECTED AND A SERVICE LETTER WILL BE ISSUED TO CHECK FOR ANY INCORRECTLY INSTALLED CABLE ASSEMBLIES OR SPARES ON HAND THAT MAY BE AFFECTED. (TC NR 20061221006)                                                                                                                                                                                                                   1H72 3T4  TRTA9EA    E4EA    6  CP15EA    
20070125003922007012500392NE  2007       1          25         CA061222002      220061217G7310AE7010000N0130  HOSE                                    CNDAIRCL604 CL604       1900301EA  GE    CF34  CF348E5A1   30015NE                              FUEL SYSTEM     TORN            W      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  NRNOT REPORTED   1                      CA                                                                      (CAN) FUEL LEAK WAS FOUND FROM HOSE ASSY P/N AE7010000N0130 AFTER THE SECOND ENGINE RUN.  NOTE: PRIOR RUN, LINE WAS REPLACED IAW (DISCLOSURE LETTER), BATCH RECALL DUE TO DEFECTIVE HOSE (BATCH NR 8740850) (TC NR 20061222002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA21EA   E00063EN             
20070125003932007012500393EU  2007       1          25         CA061222003      120061214G28000725145         ELEMENT                     0725185     AIRBUS320   A320232     3930326EU  IAE   V2527 V2527A5          NE                              REFUEL COUPLING LEAKING         W      O   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      CA                                                                      (CAN) WHILE REFUELING, IT WAS NOTICED THAT FUEL WAS LEAKING FROM THE ELEMENT ASSY.  INITIALLY IT WAS THOUGHT THAT THE COUPLING HAD BEEN DAMAGED BUT ON INSPECTING THE PART IT WAS DETERMINED THAT THE 8 SECURING SCREWS HAD ROTATED APPROX A HALF TURN LOOSE. (TC NR 20061222003)                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F4  FRTA28NM   E40NE                
20070507001962007050700196SW  2007       5          7          CA061222004      120061204G6220204011116001    NUT                                     BELL  205   205B               SW  LYC   T53   T5317A      41549NE                              MAIN ROTOR HEAD CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       14698      A49                                                 (CAN) THE ACORN NUTS WERE SENT OUT FOR NDT IAW THE REQUIREMENT OF THE OVERHAUL OF THE M/R HEAD ASSY.  THE NDT SHOP FOUND A CRACK DEVELOPING NEAR THE BASE IN THE TRANSITION AREA OR CURL  OF THE DOME AND THE GEAR PART OF THE ACORN NUTS. THE ESTIMATED TIME ON THE ACORN NUTS IS 14698 HOURS IAW M/R HEAD ASSY. (TC NR 20061222004)                                                                                                                                                                                                                                                                                                                                                                                                           1G71 4U4  U  H1SW    E17EA                
20070125003942007012500394GL  2007       1          25         CA061222005      220061208G7261                OIL SYSTEM                              LKHEED382   382G        526414USO  ALLSN 501D  501D22A     03006GL  HAMSTD54H   54H60117    NE  NR 2 ENGINE     LEAKING         W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) ENROUTE THE CREW OBSERVED LOW OIL QUANTITY ON THE NR 2 ENGINE. FLUID WAS OBSERVED DEPARTING THE DRAIN MAST.  THE ENGINE WAS SHUTDOWN AND THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WITHOUT FURTHER PROBLEM. MAINTENANCE FOUND AN AIR LEAK OCCURING AT THE OIL QUANTITY TRANSMITER ACCESS PANEL ON THE OIL TANK.  FOAMING RESULTED DUE TO LOSS OF PNEUMATIC HEAD PRESSURE CAUSING THE SYSTEM TO VENT.  THE ACCESS PANEL BOLTS WERE RETORQUED ENGINE OIL REPLENISHED.  THE AIRCRAFT WAS GROUND RU AND RETURNED TO SERVICE.                                                                                                                                                                                                                2H74 4T4  T  A1SO    E282    6  CP906     
20070125003952007012500395EU  2007       1          25         CA061222006      120061209G7712567775080       INDICATOR                               AEROSPATR42 ATR42300    8680920EU  PWA   120   PW120            NE  HAMSTD14SF  14SF5       NE  TORQUE          MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CRCRUISE         1                      CA                                                                      (CAN) ENROUTE THE CREW OBSERVED DRAMATIC FLUCTUATION IN THE NR 2 ENGINE TORQUE INDICATOR. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WITHOUT INCIDENT. AFTER TROUBLE SHOOTING MAINTENANCE REPLACED THE NR 1 TORQUE INDICATOR AND THE SYSTEM WAS CHECKED SERVICEABLE. (TC NR 20061222006)                                                                                                                                                                                                                                                                                                                                                                                                                                                       2H72 4T4  TRTA53EU   E20NE   6  CP7NE     
20070125003962007012500396CE  2007       1          25         CA061222007      120061220G24353022376         SEAL                                    BEECH 200   B200        1152922CE  PWA   PT6   PT642A           NE  HARTZLHCE4N HCE4N3      NE  ENGINE          LEAKING         W      O   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) PILOT NOTICED OIL PRESSURE FLUCTUATIONS IN CRUISE FLIGHT. ENGINE LIMITS NOT EXCEEDED AND THE AIRCRAFT LANDED AT DESTINATION. ENGINE OIL WAS LOST THROUGH A LEAKING STARTER GENERATOR DRIVE GARLOC SEAL. SEAL REPLACED WITH NEW PN 3059046-01 IAW MFG CATEGORY 8 (OPTIONAL) SB 3420. GROUND RUNS C/O SATISFACTORY AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20061222007)                                                                                                                                                                                                                                                                                                                                                                    1L72 4T4  T  A24CE   E4EA    5  CP10NE    
20070125003972007012500397EA  2007       1          25         CA061225001      120061223G77972572152545A     CONNECTOR                               CNDAIRCL600 CL600*             EA  GE    CF34  CF34*            NE                              RT ENGINE       SHORT           W      O   OTHER                                                                                           EN VIBRATION/BUFFET          FALSE WARNING                                       APAPPROACH       1                      CA                                                                      (CAN) FLIGHT CREW REPORTED ENGINE VIBRATION.  MAINTENANCE INSPECTION REVEALED A TAR LIKE SUBSTANCE ON ENGINE FAN BLADES.  SUBSTANCE ALSO FOUND ON UNDERSIDE OF FLAPS BEHIND MAIN WHEELS.  SUBSTANCE WAS CLEANED OFF AND FAN LUBE AND RUNS WERE CARRIED OUT, NO FIX VIBES STILL FLUCTUATING BETWEEN .2 AND 5.7 AT IDLE.  N1 SENSORS SWAPPED STILL NO FIX.  AFTER FURTHER INSPECTION ENGINE CONNECTOR J554 FOR THE RT ENGINE LOCATED BEHIND THE AFT CARGO BULKHEAD WAS FOUND TO HAVE AN INTERNAL SHORT.  CONNECTOR REPLACED AND AIRCRAFT FOUND SERVICEABLE. (TC NR 20061225001)                                                                                                                                                                   2L72 4F4  FRTA21EA   E15NE                
20070125003982007012500398    2007       1          25         CA061227001      420061219G349734440058        WIRE                                    AIRBUS310   A310300     3930305EU  GE    CF6   CF680C2*         GL                              AIR COLLISION   BURNED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) ON ARRIVAL, FLIGHT CREW REPORTED TCAS AND RA FAILURE FLAGS ON BOTH IVSIS DURING FLIGHT. WHILE TROUBLESHOOTING TCAS FAILURE, SEVERAL BURNED WIRES WERE DISCOVERED IN A BUNDLE LOCATED BEHIND THE ATC1 AND TCA RACK (500VU). THE WIRE SUSPECTED OF CAUSING THE DAMAGE IS THE TCAS POWER SUPPLY WIRE 3444-0058 BETWEEN CONNECTOR 221VC AND TERMINAL BOARD 1487VT MODULE AND PIN A. (REF A-310 AWM 34-44-01 PG 003 SHEET 1). ALL DAMAGED WIRES WERE REPLACED, CONNECTORS VERIFIED AND AS PRECAUTION AND MFG RECOMMENDATION THE TCAS PROCESSOR AND TCAS POWER SUPPLY CIRCUIT BREAKER WERE REPLACED.  (TC NR 20061227001)                                                                                                                      2L72 4F4  FRTA35EU   E23EA                
20070507001972007050700197CE  2007       5          7          CA061227002      120061226G79311013890235      TRANSMITTER                             BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE  HARTZLHCE4A HCE4A3I     NE  OIL PRESSURE    MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 N  FALSE WARNING                                                                 CRCRUISE         1                      CA                                                                      (CAN) ENROUTE FROM RT OIL PRESSURE INDICATED 50 PSI. THERE WAS NO CORRESPONDING R LOW ANNUNCIATOR, DECLARED AN EMERGENCY AND PERFORMED A PRECAUTIONARY SHUTDOWN OF THE RT ENGINE.  RETURNED WITHOUT INCIDENT. MAINTENANCE TROUBLESHOT INDICATION TO A FAULTY OIL PRESSURE TRANSDUCER.  NEW TRANSDUCER INSTALLED, A/C GROUND RUN WITH NO FURTHER INDICATION PROBLEMS (TC NR 20061227002)                                                                                                                                                                                                                                                                                                                                                         2L72 4T4  TRTA24CE   E26NE   5  CP10NE    
20070125003992007012500399EA  2007       1          25         CA061227003      220061222G8500                ENGINE                                  CESSNA172   172M        2072418CE  LYC   O320  O320E2D     41508EA  MCAULY1C160 1C160DTM    GL                  MAKING METAL    W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            2510                                                      (CAN) DURING SCHEDULED MAINTENANCE, AT A 200HR. INSPECTION, METAL FOUND IN OIL. METAL TURNED OUT TO BE FROM NR 3 CYLINDER CONNECTING ROD, LOWER BEARING. (TC NR 20061227003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H71 3O3  ONT3A12    E274    5  NP910     
20070125004002007012500400EA  2007       1          25         CA061227004      220061221G8500                ENGINE                                  CESSNA172   172M        2072418CE  LYC   O320  O320E2D     41508EA  MCAULY1A175 1A175ATM    GL                  MAKING METAL    W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            1452                                                      (CAN) DURING 50 HR. OIL CHANGE, HEAVY BRASS-LIKE MATERIAL WAS NOTED IN THE OIL FILTER. CYLINDER WAS REMOVED TO INSPECT ENGINE CORE. CRANKSHAFT CENTER JOURNAL BEARING WAS FOUND TO BE DISINTEGRATING. ENGINE REMOVED FROM SERVICE. (TC NR 20061227004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3O3  ONT3A12    E274    5  NP857     
20070125004012007012500401EA  2007       1          25         CA061227005      220061218G8520                CRANKSHAFT                              PIPER PA34  PA34200     7103405SO  LYC   O360  IO360C1E6   41514EA  HARTZLHCC2Y HCC2YK2     GL  ENGINE          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            1976                                                      (CAN) LT ENGINE DEVELOPED AN OIL LEAK FROM CRANKSHAFT SEAL. DURING SEAL REPLACEMENT, IT WAS NOTICED THAT THE CRANKSHAFT FLANGE WHERE PROPELLER BOLTS ON, WAS CRACKED FROM ONE LIGHTNING HOLE TO THE OTHER.  IT LOOKED AS IF THERE WAS AN INDENTATION ON THE BACK SIDE OF THE LIGHTNING HOLE. THIS IS THE POINT FROM WHICH THE CRACK APPEARED TO HAVE STARTED. THE MARK/INDENTATION APPEARS TO BE FROM A ROUND BAR BEING USED TO TURN THE CRANKSHAFT WHEN THE PROPELLER IS NOT INSTALLED. ENGINE IS BEING REMOVED FOR REPLACEMENT. (TC NR 20061227005)                                                                                                                                                                                           1L72 3O3  O  A7SO    1E10    5  CP920     
20070129003482007012900348EA  2007       1          29         CA061227006      120061227G56106003303026      WINDSHIELD                              CNDAIRCL601 CL6013A     8070802EA  GE    CF34  CF343A      30015NE                              COCKPIT         BROKEN          W      O   OTHER                                                                                           O  OTHER                                                                         APAPPROACH       1                      CA       2774                                                           (CAN) RT WINDSHIELD FACE PLY BROKEN IN FLIGHT. APPROX. 7000 INCH ON APPROACH.  FOD INSPECTION CARRIED OUT ON ENGINE INTAKE AND WINDSHIELD REPLACED.  A/C HOURS; 6836 A/C CYCLES; 7326   (TC NR 20061227006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA21EA   E15NE                
20070507001992007050700199EU  2007       5          7          CA061228001      120061221G673010546662        HOUSING                                 BOLKMS117   BK117A1     5626010EU                                                               ACTUATOR        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       2550                                                           (CAN) DURING A ROUTINE DISASSEMBLY TO CORRECT SEAL LEAKAGE A CRACK WAS FOUND AT THE LEE PLUG ON THE FRONT OF THE ACTUATOR.  THE CRACK EXTENDS UP TOWARDS THE SERVO VALVE (TC NR 20061228001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1G72 3U      H13EU                        
20070129003302007012900330GL  2007       1          29         CA061228002      220061215G7261                GASKET                                  LKHEED382   382G        526414USO  ALLSN 501D  501D22A     03006GL  HAMSTD54H   54H60117    NE  NR 1 ENGINE     FAILED          W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         K  FLUID LOSS                                                                    CRCRUISE         1                      CA                                          550302                      (CAN) AFTER DEPARTING AND CLIMBING THROUGH 10K FEET THE CREW OBSERVED A LOW OIL QUANTITY CONDITION ON NR 1 ENGINE. VISUAL CONFIRMATION OF OIL LOSS ACCOMPLISHED AND NR 1 ENGINE SHUTDOWN. THE AIRCRAFT RETURNED WITHOUT INCIDENT TO POINT OF DEPARTURE.  MAINTENANCE REPLACED THE NR 1 ENGINE SCAVENGE PUMP AND FILTER. ALSO REPLACED THE GASKET ON THE OIL TANK ACCESS PANEL FOR THE QUANTITY TRANSMITTER. THE AIRCRAFT WAS GROUND RUN AND RETURNED TO SERVICE. (TC NR 20061228002)                                                                                                                                                                                                                                                            2H74 4T4  T  A1SO    E282    6  CP906     
20070507002002007050700200CE  2007       5          7          CA061229001      120061227G32301153800025      MOTOR                                   BEECH 200   200BEECH    1152920CE  PWA   PT6   PT6A41      52043EA  HARTZLHCB3T HCB3TN3     GL  MLG             UNSERVICEABLE   W      O   OTHER                                                                                           O  OTHER                                                                         DEDESCENT        1                      CA            4                                                         (CAN) WHEN LANDING GEAR ONLY EXTENDED HALFWAY.  EMERGENCY EXTENSION USED TO EXTEND TO LANDING CONFIGURATION. MOTOR WAS INSTALLED AS AN OVERHAULED UNIT 4.4 HRS PRIOR TO FAILURE.  C/B WAS FOUND TRIPPED UNDER CABIN FLOOR. BREAKER RESET AND GEAR CYCLED. MOTOR WAS LABORING TO OPERATE. NEW MOTOR INSTALLED AND GEAR CYCLES CARRIED OUT WITH NO FAULTS FOUND. (TC NR 20061229001)                                                                                                                                                                                                                                                                                                                                                              1L72 4T4  T  A24CE   E4EA    6  CP15EA    
20070129003312007012900331EA  2007       1          29         CA061229002      120061227G3320BC10065003      RECEPTACLE                              CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30015NE                              CABIN           DAMAGED         W      A   UNSCHED LANDING                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB, PASSENGER ALERTED FA TO SMOKE SMELL IN REAR OF CABIN. SMOKE WAS THEN VISIBLY OBSERVED BY PASSENGERS AND FA. FLIGHT RETURNED TO DEPARTURE AIRPORT AND ERS WAS REQUESTED. AIRCRAFT WAS APPROX 2000 LBS OVERWEIGHT BUT LANDED AND TAXIED TO THE GATE WITHOUT FURTHER INCIDENT. TROUBLESHOOTING BY MAINTENANCE DETERMINED THAT THE SIDEWALL LIGHTING ASSEMBLY AT SEAT 6F TO BE AT FAULT. RECEPTACLE FOR LIGHT APPEARED PITTED AND MAY HAVE CAUSED LIGHT ASSEMBLY TO SHORT OUT. LIGHT ASSEMBLY WAS REPLACED WITH NO FURTHER EVIDENCE OF SMOKE OR ELECTRICAL SMELL. IAW AMM 05-51-01 PAGE 601 AND FIG 601 NO FURTHER OVER WEIGHT INSPECTIONS REQUIRED. AFTT 26345, TOTAL CYCLES 21861. (TC NR 20061229002)                        2L72 4F4  FRTA21EA   E15NE                
20070129003322007012900332NM  2007       1          29         CA070102002      120061225G5610NP15790112      WINDSHIELD                              DHAV  DHC8  DHC8*              NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  COCKPIT         CRACKED         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) F/O WINDSHIELD SHATTER IN FLIGHT AT FL20. NO EVIDENCE OF ANY IMPACT. AIRCRAFT RETURNED TO BASE AND LANDED WITHOUT ANY FURTHER INCIDENT.  WINDSHIELD ASSEMBLY WAS REPLACED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20070102002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20070129003332007012900333NE  2007       1          29         CA070102003      220061223G8500R20007M2        ENGINE                                  DOUG  DC4   C54EDC      3021528WP  PWA   R2000 R20007M2    52023NE  HAMSTD23E   23E50       NE                  MAKING METAL    W      E   ENGINE SHUTDOWN                                                                                 EK VIBRATION/BUFFET          FLUID LOSS                                          NRNOT REPORTED   1                      CA                                                                      (CAN) ENGINE BEGAN TO RUN ROUGH, DECREASE IN OIL PRESSURE, ENGINE WAS SHUTDOWN AND FEATHERED.  OIL SCREEN PULLED, MODERATE AMOUNT OF ALUMINUM FILINGS, ENGINE REMOVED AND SENT FOR OVERHAUL.  NOTE: SUSPECT LINK PIN (TC NR 20070102003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L74 4R4  R  A762    5E5     6  CP603     
20070129003362007012900336EA  2007       1          29         CA070102004      120061219G2752                ACTUATOR                                CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              T/E FLAP        EXCESS PLAY     W      O   OTHER                                                                                           FJ FLT CONT AFFECTED         WARNING INDICATION                                  APAPPROACH       1                      CA                                                                      (CAN) ON APPROACH (FLAPS FAIL) CAUTION MESSAGE APPEARED WHEN THE CREW SELECTED FLAPS FROM 30 - 45 DEG. ON LANDING.  MAINTENANCE INSPECTED THE A/C FLAP SYSTEM AND FOUND RT AND LT IB FLAP (O/B ACTUATORS HAD EXCESSIVE SIDE PLAY OVER 0.015) IAW AMM 27-53-01-400-801, ALSO RT NR3 AND NR5 FLEX DRIVES FOUND DEFECTIVE.  ALL COMPONENTS WERE REPLACED AND THE A/C WAS RETURNED TO SERVICE UPON A SATISFACTORY TEST FLIGHT .  FLAPS FAILED ON FINAL APPROACH AT 30 DEG.  FURTHER INSP. WAS CARRIED OUT ON THE FLAP SYSTEM AND THE IB NR1 FLAP ACTUATORS WERE REPLACED DUE TO EXCESSIVE FORE AND AFT PLAY AND THE FLAP DRIVE UNIT WAS REPLACED.  THE FLAP SYSTEM WAS RIGGED IAW AMM 27-53-00 AND GROUND/FUNCTION CHECKED SERVICEABLE.  THE A/C WAS2L72 4F4  FRTA21EA   E15NE                
20070129003402007012900340EU  2007       1          29         CA070103002      120061229G561066642023        WINDSHIELD                              AIRBUS320   A320214     3930316EU  CFMINTCFM56 CFM565B4P        NE                              COCKPIT         CRACKED         W      O   OTHER                                                                                           M  OVER TEMP                                                                     NRNOT REPORTED   1                      CA                                                                      (CAN) WINDOW HEAT CONTROLLER MALFUNCTIONED CAUSING CAPT WINDSHIELD OUTER PLY TO CRACK. (TC NR 20070103002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F4  FRTA28NM   E38NE                
20070129003412007012900341NE  2007       1          29         CA070103003      220061201G7200PT6A42          ENGINE                                  PIPER PA46  PA46500TP   7104622SO  PWA   PT6   PT6A42      52043NE                                              MALFUNCTIONED   W      O   OTHER                                                                                           R  PARTIAL RPM/PWR LOSS                                                          CLCLIMB          1                      CA                                                                      (CAN) THE ENGINE WAS REPORTED TO LOSE POWER SHORTLY AFTER TAKEOFF, RESULTING IN A FORCED LANDING AND DAMAGE TO THE AIRCRAFT.  MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070103003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1L71 3O4  TRTA25SO   E4EA                 
20070129003422007012900342NM  2007       1          29         CA070103004      120061226G27303906001007      PCU                                     BOMBDRDHC8  DHC8400            NM  PWC   150   PW150A           EA  ROTOL R408  CR4086123F17EU  RT ELEVATOR     DAMAGED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       299                                                            (CAN) MAINTENANCE NOTICE RT ELEVATOR DROOP WHEN PARKED. FURTHER INVESTIGATION FOUND BROKEN NR 3 RT PCU.  ELEVATOR PCU FAILURE CAUSED DAMAGE TO THE HORIZONTAL STABILIZE STRUCTURE.  (TC NR 20070103004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2H72 4T4  TRTA13NM   E00062EN6  CP17BO    
20070129003432007012900343    2007       1          29         CA070103005      220061203G7321                SEAL                                    AMD   FALC50FALCON2000  2730170NM              PW308C                                           FUEL CONTROL    LEAKING         W      E   ENGINE SHUTDOWN                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA                                                                      (CAN) ENGINE OIL PRESSURE WAS REPORTED TO FLUCTUATE AND GRADUALLY DECREASE IN CRUISE.  THE ENGINE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED A LEAKING FUEL CONTROL DRIVE SEAL. (TC NR 20070103005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2K72 4F    RTA50NM                        
20070129003442007012900344NE  2007       1          29         CA070103006      220061207G726130B336201       CARBON SEAL                             DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              ENGINE          LEAKING         W      E   ENGINE SHUTDOWN                                                                                 KJ FLUID LOSS                WARNING INDICATION                                  DEDESCENT        1                      CA                                                                      (CAN) DURING DESCENT THE ENGINE LOW OIL PRESSURE WARNING ACTIVATED AND THE ENGINE WAS SHUTDOWN IN FLIGHT.  SUBSEQUENT INSPECTION REVEALED A LEAKING CARBON SEAL AT THE FUEL CONTROL DRIVE PAD. (TC NR 20070103006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2H72 4T4  FRTA55NM   E35NE                
20070129001912007012900191NE  2007       1          29         CA070103007      220061211G7261                PUMP                                    GULSTM200   200         4500308NM  PWC   PW306 PW306A      52165NE                              ENGINE          MALFUNCTIONED   W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) ENGINE OIL PRESSURE WAS REPORTED TO GRADUALLY DECREASE AND THE ENGINE WAS SHUTDOWN IN FLIGHT.  THE AIRCRAFT DIVERTED FOR AN UNSCHEDULED LANDING.  THE ENGINE OIL PRESSURE PUMP WAS SUBSEQUENTLY REPLACED. (TC NR 20070103007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F4  FRTA53NM   E35NE                
20070129001922007012900192NE  2007       1          29         CA070103008      220061209G7200PW305A          ENGINE                                  LEAR  60    60LEAR      5170707CE  PWA   305   PW305A      52128NE                                              FIRE            W      E   ENGINE SHUTDOWN                                                                                 A  FLAME/FIRE                                                                    TXTAXI/GRND HDL  1                      CA                                                                      (CAN) ON START, FLAMES WERE SEEN EXITING THE ENGINE EXHAUST.  THE START WAS ABORTED.  MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070103008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA10CE   E35NE                
20070129001932007012900193EA  2007       1          29         CA070103009      220061210G7250                TURBINE BLADES                          EMB   110   EMB110P1    3260122SO  PWA   PT6   PT6A34      52043EA  HARTZLHCB3T HCB3TN3     GL  ENGINE          FRACTURED       W      E   ENGINE SHUTDOWN                                                                                 ZRASIGNIFICANT FAILURE REPORTPARTIAL RPM/PWR LOSS      FLAME/FIRE                CRCRUISE         1                      CA                                          42192                       (CAN) DURING CRUISE ENGINE POWER REDUCED UNCOMMANDED, ACCOMPANIED BY A LOUD NOISE AND FLAMES EXITING THE EXHAUST.  SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES AND A SEIZED REDUCTION GEARBOX.  MFG WILL MONITOR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070103009)                                                                                                                                                                                                                                                                                                                                                                                                                    1L72 4T4  T  A21SO   E4EA    6  CP15EA    
20070129001942007012900194EA  2007       1          29         CA070103010      220060911G7200PT6A34          ENGINE                                  EMB   110   EMB110*            SO  PWA   PT6   PT6A34      52043EA                                              FLAMED OUT      W      O   OTHER                                                                                           X  ENGINE FLAMEOUT                                                               NRNOT REPORTED   1                      CA                                                                      (CAN) THE ENGINE FLAMED OUT IN FLIGHT ACCOMPANIED BY A LOUD NOISE.  MFG WILL INVESTIGATE THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070103010)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L72 4T4  TRTA21SO   E4EA                 
20070129001962007012900196EA  2007       1          29         CA070104001      120061224G5610NP13932200      WINDOW                                  CNDAIRCL600 CL6002B19   1900309EA                                                               COCKPIT         UNKNOWN         W      K   NONE                                                                                            O  OTHER                                                                         CRCRUISE         1                      CA       11983                                                          (CAN) MAINTENANCE REPLACED SIDE WINDOW. (TC NR 20070104001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F    RTA21EA                        
20070129001972007012900197NE  2007       1          29         CA070104002      220061224G73216078T39P03      FCU                                     CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30015NE                              LT ENGINE       MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 F  FLT CONT AFFECTED                                                             APAPPROACH       1                      CA       10542                                                          (CAN) (DIVERTED, WITH ENGINE PROBLEMS, CREW CALLED WHEN ON GROUND.  ON APPROACH, THE LT ENGINE WOULD NOT IDLE BACK BELOW 79 PERCENT N1. IT WOULD RESPOND TO INPUTS ABOVE 79 PERCENT.  CREW ELECTED TO SHUTDOWN THE ENGINE, AND DIVERT.)  MX WAS UNABLE TO DUPLICATE THIS PROBLEM, WHILE INITIATING START, N1 RAN AWAY SHORTLY AFTER LIGHT OFF.  MX REPLACED FCU. (TC NR 20070104002)                                                                                                                                                                                                                                                                                                                                                            2L72 4F4  FRTA21EA   E15NE                
20070129001982007012900198EA  2007       1          29         CA070105001      120061230G5350                RADOME                                  CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343A1     30015NE                              FUSELAGE        BIRD STRIKE     W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA                                                                      (CAN) AFTER DEPARTURE CREW WITNESSED A BIRD STRIKE ON THE NOSE OF THE AIRCRAFT. CREW ELECTED TO RETURN TO DEPARTURE AIRPORT AND LAND OVERWEIGHT (ESTIMATED AT 49200 LBS). AIR TRAFFIC CONTROL WAS NOTIFIED BUT EMERGENCY EQUIPMENT WAS NOT REQUIRED.  MAINTENANCE INSPECTION DISCOVERED A DEAD SEAGULL WHICH HAD PENETRATED THE RADOME DAMAGING THE WEATHER RADAR ANTENNA AND THE NOSE BULKHEAD. FDR REMOVED FOR READING. FURTHER OVERWEIGHT LANDING INSPECTION NOT REQUIRED IAW FDR READOUT AND AMM 05-51-01 PAGE 609, SUBTASK 05-51-01-970-004 FOR IMPACT SPEED OF 120 FT/MIN. THE FOLLOWING PART REPLACEMENTS WERE COMPLETED: FDR P/N S800-20000-00. ULB DK120. RADOME P/N 4926-201. WEATHER RADAR ANTENNA P/N 622-9302-003. DAMAGE TO BULKHE2L72 4F4  FRTA21EA   E15NE                
20070129001992007012900199EA  2007       1          29         CA070105002      220061216G7250                TURBINE BLADES                          DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A27      52043EA  HARTZLHCB3T HCB3TN3     GL  ENGINE          FRACTURED       W      O   OTHER                                                                                           JY WARNING INDICATION        ENGINE STOPPAGE                                     CRCRUISE         1                      CA                                                                      (CAN) ENGINE OIL PRESSURE WERE REPORTED TO FLUCTUATE IN CRUISE FOLLWED BY A LOUD NOISE AND AN UNCOMMANDED ENGINE SHUTDOWN.  SUBSEQUENT INSPECTION REVEALED METAL DEBRIS IN THE ENGINE OIL AND FRACTURED POWER TURBINE BLADES.  MFG WILL MONITOR INVESTIGATION OF THE EVENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070105002)                                                                                                                                                                                                                                                                                                                                                                                                       1H72 3T4  TRTA9EA    E4EA    6  CP15EA    
20070129002002007012900200NE  2007       1          29         CA070105003      220061214G7250                TURBINE BLADES  PWC         PT6A114A    CESSNA208   208B        2073701CE  PWA   PT6   PT6A114A    52043NE                              ENGINE          FRACTURED       W      O   OTHER                                                                                           Y  ENGINE STOPPAGE                                                               CRCRUISE         1                      CA                  19232                   19232                       (CAN) THE ENGINE SUFFERED AN INFLIGHT SHUTDOWN IN CRUISE.  SUBSEQUENT INSPECTION REVEALED THE AIRFRAME INLET AIR BOX PARTIALLY OPEN WITH A FASTENING PIN MISSING.  THE ENGINE COMPRESSOR WAS FOUND STIFF TO ROTATE WITH DAMAGE EVIDENT TO THE SECOND STAGE STATOR AND THE POWER TURBINE BLADES WERE FOUND FRACTURED.  MFG WILL MONITOR INVESTIGATION OF THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070105003)                                                                                                                                                                                                                                                                                                             1H71 3T3  T  A37CE   E4EA                 
20070129002032007012900203EA  2007       1          29         CA070106001      120061227G3320BC10065005      RECEPTACLE                              CNDAIRCL600 CL6002B19   1900309EA                                                               CABIN           FAULTY          W      A   UNSCHED LANDING                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMBOUT PASSENGER ALERTED FA TO SMOKE SMELL IN REAR OF CABIN , SMOKE WAS THEN VISIBLY OBSERVED BY PASSENGERS AND FA. FLIGHT RETURNED TO DEPARTURE AIRPORT AND ERS WAS REQUESTED. AIRCRAFT WAS APPROX. 2000 LBS OVERWEIGHT BUT LANDED AND TAXIED TO THE GATE WITHOUT FURTHER INCIDENT.  MAINTENANCE DETERMINED THAT THE SIDEWALL LIGHTING ASSEMBLY AT SEAT 6F TO BE AT FAULT. RECEPTACLE FOR LIGHT APPEARED PITTED AND MAY HAVE CAUSED LIGHT ASSEMBLY TO SHORT OUT. LIGHT ASSEMBLY WAS REPLACED IAW AMM 05-51-01 PAGE 601   (TC NR 20070106001)                                                                                                                                                                                    2L72 4F    RTA21EA                        
20070508001932007050800193EU  2007       5          8          CA070108004      120061221G6320350A32315520    CASE HALF                               SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1        NE                              GEAR BOX        WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            3727                                                      (CAN) HALF SHELLS WERE WORN OUT DUE TO MOVEMENT OF THE SUN GEAR, WEARING S STEP INTO THE SHELLS. THERE IS NO PUBLISHED LIMITS ON THE SHELLS AND WE HAVE ASKED ECL FOR THIS INFORMATION. THERE IS NORMAL WEAR IN THIS AREA, THIS WAS A BIT EXCESSIVE WITH SLIVERS OF METAL COMING OFF THE PARTS. THIS WOULD HAVE LEAD TO A CHIP LIGHT EVENTUALLY. (TC NR 20070108004)                                                                                                                                                                                                                                                                                                                                                                            1G71 3U3  U  H9EU    E19EU                
20070129002112007012900211EA  2007       1          29         CA070108005      120061228G4930388273010       FCU                                     CNDAIRCL600 CL6002B19   1900309EA  GE    CF34  CF343B1          NE                              APU             LEAKING         W      O   OTHER                                                                                           K  FLUID LOSS                                                                    TXTAXI/GRND HDL  1                      CA       396  396                                                       (CAN) DEC 28/06, AERO CALLOUT 061228/01, ON PUSHBACK, A RAMP AGENT NOTICED A PUDDLE OF FUEL ON THE GROUND AT THE BACK OF THE AIRCRAFT.  APPARENTLY, FUEL WAS LEAKING FROM THE APU. THE CAPTAIN CHECKED THE LEAK  AS F/O CALLED APRON.  THE FIRE TRUCKS WERE CALLED AS WELL AS CONSOLIDATED FUELERS TO CLEAN UP THE AREA.  THE PASSENGERS WERE DEPLANED AS A PRECAUTION.  MAINTENANCE CONFIRMED THAT THE LEAK WAS FROM THE APU FCU DRAIN LINE, THEY THEN DEFERRED THE APU AND THE A/C DEPARTED WITHOUT INCIDENT.  THE FCU WAS REPLACED AND LEAK CHECKS WERE CARRIED OUT.  TEARDOWN REPORT TO FOLLOW. (TC NR 20070108005)                                                                                                                         2L72 4F4  FRTA21EA   E15NE                
20070129002122007012900212NM  2007       1          29         CA070108006      120061227G322288295           NUT             MESSIER     8800121     DHAV  DHC8  DHC8106     2809020NM  PWA   PW121 PW121       52124NE  HAMSTD14SF  14SF7       NE  NLG             BROKEN          W      K   NONE                                                                                            O  OTHER                                                                         TOTAKEOFF        1                      CA                  DCL051085                                           (CAN) SUSPECT CAP NUT SHEARED UPON TAKEOFF DUE TO THE UNEVEN RUNWAY.  REF ATTACHED PILOTS REPORTS AND PHOTO`S OF DAMAGED CAP NUT.   (TC NR 20070108006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
20070508001942007050800194EU  2007       5          8          CA070108007      120061219G2910MS2771923       SWITCH                                  SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1        NE                              COLLECTIVE      INTERMITTENT    W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) PROBLEM REPORTED BY PILOT IN DECEMBER ABOUT INTERMITTENT SWITCH. THIS HAPPENED ONCE IN THE FIELD. THE A/C WAS BROUGHT IN FOR AN INSPECTION AT THE END OF DECEMBER/06 AND THE SWITCH WAS REPLACED.  BAD SWITCHES, SHOULD BE REPLACED WITH SOMETHING BETTER. (TC NR 20070108007)                                                                                                                                                                                                                                                                                                                                                                                                                                                            1G71 3U3  U  H9EU    E19EU                
20070129002142007012900214EA  2007       1          29         CA070109001      120061207G2820600624623       TUBE                                    CNDAIRCL604 CL604       1900301EA  GE    CF34  CF343B1          NE                              FUEL SYSTEM     BLOCKED         W      O   OTHER                                                                                           K  FLUID LOSS                                                                    TXTAXI/GRND HDL  1                      CA       65                                                             (CAN) AUTO SHUTOFF DID NOT OCCUR DURING PRESSURE REFUELING OPERATIONS RESULTING IN FUEL SPILL ON RAMP. OPERATOR REPORTED SIMILAR PROBLEMS SINCE TAKING DELIVERY OF NEW AIRCRAFT. IT WAS FOUND THAT A NUMBER OF LT AND RT WING TRANSFER AND BALANCING PIPES (TUBES) HAD BEEN PARTIALLY OBSTRUCTED AT THE CONNECTING JOINTS BY SEALANT. AIRCRAFT OEM FIELD SERVICE REPRESENTATIVES WERE ON SITE FOR RECTIFICATIONS. (TC NR 20070109001)                                                                                                                                                                                                                                                                                                           2L72 4F4  FRTA21EA   E15NE                
20070129002202007012900220EA  2007       1          29         CA070109003      120061227G5220H341935         HOUSING                                 CNDAIRCL600 CL6002B19   1900309EA                                                               ESCAPE HATCH    CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       867                                                            (CAN) ESCAPE HATCH OUTER HANDLE HOUSING WAS FOUND CRACK DURING AN AFTER STORAGE RETURNED TO SERVICE.  INVESTIGATION IS IN PROGRESS. (TC NR 20070109003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F    RTA21EA                        
20070129002212007012900221EU  2007       1          29         CA070109005      120061108G28101608565         VALVE                                   FOKKERF28   F28MK0100   4990807EU  RROYCETAY   TAY65015    54557NE                              FUEL SYSTEM     MALFUNCTIONED   W      D   RETURN TO BLOCK                                                                                 K  FLUID LOSS                                                                    TXTAXI/GRND HDL  1                      CA                                                                      (CAN) DATE OF DELAY NOV 8, 2006 CADORS NR: 2006C2915.  THE FLIGHT CREW WAS NOTIFIED THAT DURING TAXI FOR DEPARTURE FUEL WAS LEAKING FROM LT WING.    AIRCRAFT TAXIED OFF RUNWAY BY WHICH TIME THE LEAK HAD STOPPED. FLIGHT CREW IN CONTACT WITH MAINTENANCE CONTROL AGREED THAT THE LEAK WAS FROM THE WING TANK VENTING SYSTEM.  AFTER THE SPILL WAS CLEANED, AC DEPARTED.  FOLLOW UP ACTION, THIRD OCCURRENCE OF FUEL LEAK FROM THE VENT SYSTEM ON THIS AIRCRAFT. THE FIRST EVENT WHICH OCCURRED OCT 28 WAS RECTIFIED WITH REPLACEMENT OF THE SUCTION RELIEF VALVE. SNAG RETURNED NOV 3 AT WHICH TIME MAINTENANCE REFUEL AND DE-FUEL THE AIRCRAFT SEVERAL TIMES AND COULD NOT FAULT THE SYSTEM. IN FOLLOW UP TO THIS LATEST SNAG, WE HAVE AN EN2L72 4F4  FRT        E25NE                
20070129002232007012900223SO  2007       1          29         CA070109007      220061206G8530AEC648009PL     PISTON RING                                                                CONT  O470  O470*       17026SO                              ENGINE          SEPARATED       W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       45                                                             (CAN) MATERIAL FROM THE FACE OF THE TOP COMPRESSION RING HAD FLAKED AWAY ON CYLINDER NR 2 (TC NR 20070109007).                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         3  O          E273                 
20070129002252007012900225NM  2007       1          29         CA070110002      120061217G5610                WINDOW                                  BOEING737   737210C     1384459NM  PWA   JT8   JT8D9A      52048NE                              COCKPIT         CRACKED         W      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      CA                                                                      (CAN) DURING DEPARTURE THE RT NR 3 FLT DECK WINDOW SHATTERED. THE AIRCRAFT RETURNED TO POINT OF DEPARTURE WITHOUT FURTHER PROBLEM. THE AIRCRAFT MOVED TO MAINTENANCE BASE UNDER MEL AUTHORITY WHERE A REPLACEMENT WINDOW WAS INSTALLED. (TC NR 20070110002)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F4  F  A16WE   E2EA                 
20070129002262007012900226CE  2007       1          29         CA070110003      120061220G322205430358        TORQUE LINK                             CESSNA172   172D        2072410CE  LYC   O360  O360A1A     41514EA  HARTZLHCC2Y HCC2YK1     GL  NLG             CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       3691                                                           (CAN) PRIOR TO INSTALLATION ON AIRCRAFT, NOSE GEAR SHOCK STRUT ASSEMBLY WAS THOROUGHLY INSPECTED.  SEVERAL CRACKS WERE FOUND ON UPPER TORQUE LINK.  NEW MFG PART WAS INSTALLED. (TC NR 20070110003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H71 3O3  ONT3A12    E286    5  CP920     
20070129002272007012900227    2007       1          29         CA070110005      420061009G2340                WARNING SYSTEM              6225342001  FOKKERF28   F28MK0100   4990807EU  RROYCETAY   TAY65015    54557NE                              COCKPIT         MALFUNCTIONED   W      O   OTHER                                                                                           P  NO WARNING INDICATION                                                         LDLANDING        1                      CA                  3054                                                (CAN) THE REFERENCED AIRCRAFT AN EVENT INVOLVING THE AUTOMATIC SILENCING OF CABIN CHIMES.   NORMALLY THE FLIGHT CREW WILL ADVISE THE FLIGHT ATTENDANTS TO TAKE THEIR POSITIONS FOR LANDING WITH 3 CHIMES SELECTED MANUALLY IN THE COCKPIT.  IT APPEARS HOWEVER IN LANDING CONFIGURATION THAT THE CHIMES ARE SILENCED AND STORED UNTIL THE NR 1 ENGINE IS SHUT DOWN.  THE CHIMES ARE INHIBITED  AT CERTAIN FLIGHT PHASES.  AS INDICATED MAINTENANCE WAS ABLE TO DUPLICATE THE FAULT.  BY PUTTING THE AIRCRAFT INTO FLIGHT MODE.  ONCE THE AIRCRAFT WAS PUT BACK INTO GROUND MODE (ENGINES NOT RUNNING) THE STORED CHIMES SOUNDED.  WE HAVE POSED THIS ISSUE TO MFG.  WE HAVE REVIEWED THE SBS SL AND SEDS BUT FOUND NO INFORMATION  PERTAINING2L72 4F4  FRT        E25NE                
20070129002282007012900228SO  2007       1          29         CA070111001      120061224G3260                SWITCH                                  LKHEED382   382G        526414USO  ALLSN 501D  501D22A     03006GL  HAMSTD54H   54H60117    NE  RT MLG          MALFUNCTIONED   W      O   OTHER                                                                                           N  FALSE WARNING                                                                 CLCLIMB          1                      CA                                                                      (CAN) DURING DEPARTURE THE RT MLG CONTINUED TO INDICATE DOWN AND LOCKED AFTER THE GEAR WAS SELECTED UP. THE AIRCRAFT CONTINUED TO DESTINATION, ENROUTE THE GEAR WAS CONFIRMED UP. THE GEAR WAS VISUALLY CONFIRMED AND THE AIRCRAFT LANDED WITHOUT FURTHER PROBLEM.  MAINTENANCE REPLACED THE RT MLG FORWARD MICROSWITCH AFTER A SATISFACTORY GEAR SWING THE AIRCRAFT WAS RETURNED TO SERVICE. (TC NR 20070111001)                                                                                                                                                                                                                                                                                                                               2H74 4T4  T  A1SO    E282    6  CP906     
20070129002372007012900237    2007       1          29         CA070111014      420061230G34257004544713      SYMBOL GENERATOR                        AEROSPATR42 ATR42300    8680920EU  PWA   120   PW120            NE  HAMSTD14SF  14SF5       NE  NR 1            FAILED          W      A   UNSCHED LANDING                                                                                 I  FLT. ATTITUDE INST.                                                           CRCRUISE         1                      CA                                                                      (CAN) THE CAPTAINS EFIS SCREEN CIRCUIT BREAKER TRIPPED. THE BREAKER WAS RESET AND TRIPPED AGAIN AND THE AIRCRAFT RETURNED TO POINT OF DEPARTURE. MAINTENANCE REPLACED THE NR 1 SYMBOL GENERATOR UNIT (SGU)THE AIRCRAFT WAS RETURNED TO SERVICE AFTER SATISFACTORY FUNCTION CHECK COMPLETED. (TC NR 20070111014)                                                                                                                                                                                                                                                                                                                                                                                                                                 2H72 4T4  TRTA53EU   E20NE   6  CP7NE     
20070131001082007013100108NE  2007       1          31         CA070111016      220061219G7230FW34114         FAN BLADE                               BOMBDRBD700 BD7001A10   1390006GL  RROYCEBR700 BR700710A22009500NE                              LT ENGINE       SEPARATED       W      O   OTHER                                                                                           Y  ENGINE STOPPAGE                                                               CLCLIMB          1                      CA       650                                                            (CAN) DURING CLIMB AT APPROXIMATELY 35,000 FEET, THE CREW HEARD A LOUD BANG AND THE LT ENGINE SHUTDOWN.  THE CREW DECLARED AN EMERGENCY AND LANDED UNEVENTFULLY.  AN INSPECTION OF LT ENGINE REVEALED ONE FAN BLADE HAD FRACTURED JUST ABOVE THE ROOT. THE BLADE ROOT WAS STILL ATTACHED AND THE FRACTURED PORTION WAS RECOVERED.  DAMAGE WAS ALSO FOUND ON THE INSIDE OF THE INLET, TO SOME OF THE OTHER FAN BLADES AND TO THE GUIDE VANES. THE FAILURE WAS COMPLETELY CONTAINED AND NO DAMAGE WAS FOUND ON THE EXTERIOR OF THE NACELLE OR AIRCRAFT STRUCTURE. (TC NR 20070111016)                                                                                                                                                             2L72 4F4  FRTT00003NYE00061EN             
20070509000652007050900065EU  2007       5          9          CA070112001      120061209G55409408328506      BEARING                                 PILATSPC12  PC1245      7090551EU  PWA   PT6   PT6A67B     52043NE  HARTZLHCE4A HCE4A3D     GL  RUDDER          WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) DURING INSPECTION OF TAIL TOP ATTACH BOLT FOUND TO HAVE EXCESSIVE WEAR. RUDDER REMOVED FOR REPAIR. DURING REPAIR ANCHOR NUT WAS DAMAGED. NEW OVERSIZED BUSHING INSTALLED, WITH NEW BOLT, BEARING AND ANCHOR NUT. MFG WAS NOTIFIED OF THIS DEFECT. (TC NR 20070112001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L71 3T4  TRTA78EU   E26NE   5  CP210NE   
20070509000742007050900074NE  2007       5          9          CA070115006      120061214G632092351510042     GEARBOX                                 SKRSKYS92   S92A               NE                                                               MAIN ROTOR      MALFUNCTIONED   W      C   ABORTED TAKEOFF                                                                                 J  WARNING INDICATION                                                            LDLANDING        1                      CA       2076 2076                                                      (CAN) MAIN GEARBOX HAD SEVERAL OCCURENCES OF OIL PRESSURE DROPPING TO THE PRECAUTIONARY RANGE IN OPERATION.  (TC NR 20070115006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2G72 4U      R00024BO                     
20070129002672007012900267NE  2007       1          29         CA070115008      220061009G7250ARRIEL2B        ENGINE                                  SNIAS 350   AS350B3     8680954EU  TMECA ARRIELARRIEL2B         NE                                              FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA       709                                                            (CAN) AIRCRAFT FAILED POWER CHECK: ON INSPECTION ON WHY WE DID A BORESCOPE INSPECTION ON THE ENGINE AND FOUND THAT WE HAD A POSSIBLE TURBINE RUB. AS THIS ENGINE IS A RENTAL FROM MFG, WE CHANGED OUT THE MODULE 2 AND 3 AND SENT IT BACK TO THEM. THE NEW M02 AND M03 MODULES FIXED OUR FAILED POWER CHECK.  WE DO NOT KNOW FOR SURE WHAT CAUSED OUR PROBLEM.  (TC NR 20070115008)                                                                                                                                                                                                                                                                                                                                                             1G71 3U3  U  H9EU    E00054EN             
20070129002722007012900272NE  2007       1          29         CA070115009      220061217G7310AE7010000N0130  FUEL LINE                               CNDAIRCL604 CL604       1900301EA  GE    CF34  CF348E5A1   30015NE                              ENGINE          TORN            W      O   OTHER                                                                                           K  FLUID LOSS                                                                    NRNOT REPORTED   1                      CA                                                                      (CAN) FUEL LEAK WAS FOUND FROM HOSE ASSEMBLY P/N AE7010000N0130 ON THE SECOND ENGINE RUN AFTER THAT HOSE WAS REPLACED.  NOTE: THIS LINE WAS REPLACED AS REQUESTED BY MFG (DISCLOSURE LETTER), BATCH RECALL DUE TO DEFECTIVE HOSE (BATCH NR 840850).  (TC NR 20070115009)                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F4  FRTA21EA   E00063EN             
20070129002962007012900296EA  2007       1          29         CA070115010      220061216G72503013102         TURBINE         PWC         PT6A27      DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A27      52043EA  HARTZLHCB3T HCB3TN3     GL  ENGINE          DISINTEGRATED   W      A   UNSCHED LANDING                                                                                 YJ ENGINE STOPPAGE           WARNING INDICATION                                  CRCRUISE         1                      CA            2741  PCE41266                                            (CAN) DURING CRUISE FLIGHT, THE CREW NOTICED OIL PRESSURE ON THE NR 2 ENGINE FLUCTUATING BETWEEN 60-70 PSI, WITHIN SECONDS THE TQ PRESSURE STARTED TO FLUCTUATE. THE ENGINE MADE 3 BIG BANGS AND SHUTDOWN. THE CREW LANDED THE AIRCRAFT AT THE NEAREST AIRPORT WITHOUT INCIDENT. MAINTENANCE FOUND METAL IN THE OIL FILTER AND IN THE RGB. MOST OF THE PT BLADES EXITED THE EXHAUST. ENGINE SENT TO OVERHAUL SHOP FOR INVESTIGATION. (TC NR 20070115010)                                                                                                                                                                                                                                                                                        1H72 3T4  TRTA9EA    E4EA    6  CP15EA    
20070129003012007012900301WP  2007       1          29         CA070115011      220061126G72603586763         PLANETARY GEAR                                                             GARRTTTPE331TPE33110UG  01514WP                              ENGINE          DAMAGED         W      O   OTHER                                                                                           O  OTHER                                                                         ININSP/MAINT     1                      CA            206                                                       (CAN) UPON DOING A OIL SAMPLE, METAL WAS NOTED IN THE OIL FILTER. THE ENGINE P-63235C WAS REMOVED. ENGINE WAS FORWARDED TO THE ENGINE SHOP FOR INSPECTION OF THE METAL AND FOUND THAT 1 PLANETARY GEAR WITH THE INNER RACE PEELING METAL AND 3 PLANETARY GEARS WITH PITTING ON THE GEAR TEETH. ALL 4 PLANETARY GEARS HAVE 205.9 HRS SINCE O/H. (TC NR 20070115011)                                                                                                                                                                                                                                                                                                                                                                                     4  T          E4WE                 
20070820000352007082000035SW  2007       8          20         CA070115012      120061214G5312320035501       ANGLE                                   GULSTM690TP 690D        3970405SW  GARRTTTPE331TPE3315     01514WP  ROTOL R306  R306382F7   GL  BULKHEAD        CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       16737                                                          (CAN) FLIGHT CREW REPORTED LOWER THAN NORMAL CABIN DIFFERENTIAL PRESSURE. A GROUND PRESSURIZATION CHECK WAS CARRIED OUT AND FOUND LEAK IN AREA OF AFT PRESSURE BULKHEAD LOWER SECTION. FURTHER INSPECTION REVEALED A CRACK IN THE BEND RADIUS OF ANGLE P/N 320035-501.  P/N M690003-4 FIGURE 2-56D ITEM II. NEW ANGLE INSTALLED AND SEALED. GROUND PRESSURIZATION CHECK CARRIED OUT OKAY. (TC NR 20070115012)                                                                                                                                                                                                                                                                                                                                   1H72 3T4  T  2A4     E4WE    6  CP8EU     
20070820000362007082000036SW  2007       8          20         CA070115013      120061219G57201101918         FILLET                                  GULSTM690TP 690D        3970405SW  GARRTTTPE331TPE3315     01514WP  ROTOL R306  R306382F7   GL  RT WING         CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       16738                                                          (CAN) DURING INSPECTION OF THE AIRCRAFT A CRACK WAS SUSPECTED IN THE RT UPPER FILLET WING TO FUSELAGE.  NON DESTRUCTIVE TESTING CONFIRMED (2) CRACKS, 25 MM AND 18 MM LENGTH.  LT UPPER FILLET INSPECTED BY NDT AND NO CRACKS FOUND. AN APPROVED REPAIR CARRIED OUT.  (TC NR 20070115013)                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H72 3T4  T  2A4     E4WE    6  CP8EU     
20070129003062007012900306    2007       1          29         CA070117001      420061216G22154015373823      SERVO                                   BOMBDRBD700 BD7001A10   1390006GL  RROYCEBR700 BR700710A22009500NE                              AUTOPILOT SYS   MALFUNCTIONED   W      A   UNSCHED LANDING                                                                                 F  FLT CONT AFFECTED                                                             CRCRUISE         1                      CA                                                                      (CAN) THE OPERATOR REPORTED AILERON CONTROL DIFFICULTIES AT FL470 WHILE ENROUTE.  THE AIRCRAFT DEPARTED IN HEAVY RAIN.  THE PILOT-IN-COMMAND (PIC) DISCONNECTED THE AUTOPILOT AFTER AN AP TRIM IS LWD CAS MESSAGE WAS ANNUNCIATED AND NOTED THAT THE AILERON CONTROL WHEELS WOULD NOT ROTATE WHEN ATTEMPTED BY HAND.  THE CREW OVERPOWERED THE CONDITION AND THEN ELECTED TO DESCEND TO A LOWER ALTITUDE.   THE PIC STATED THAT AT APPROXIMATELY FL440 THE CONTROL WHEEL LOCKED UP AGAIN AND THE CONDITION WAS OVERPOWERED BY THE CREW.  THE FORCE APPLIED TO OVERPOWER THE CONTROL WHEEL FOR BOTH OCCURRENCES WAS APPROXIMATELY 20 LBS.  THE PIC ALSO STATED THAT THE AILERON CONTROL SYSTEM WAS BACK TO NORMAL FOR THE DURATION OF THE FLIGHT 2L72 4F4  FRTT00003NYE00061EN             
20070509001912007050900191    2007       5          9          CA070118007      420061207G34170102AH2AF       PROBE                                   BOMBDRBD700 BD7001A10   1390006GL  RROYCEBR700 BR700710A22009500NE                              TAT             MALFUNCTIONED   W      O   OTHER                                                                                           F  FLT CONT AFFECTED                                                             CRCRUISE         1                      CA       372                                                            (CAN) DURING CRUISE AT 43,000 FEET, CREW HAD EICAS MESSAGE AIR DATA COMPUTER (ADC) 3 MISCOMPARE ANNUNCIATED FOR 2 MINUTES FOLLOWED MOMENTARILY BY ADC 1 MISCOMPARE AND THEN ADC 2 MISCOMPARE MESSAGES.  AFTER THE MESSAGES WENT OUT, COCKPIT INDICATIONS STARTED TO SHOW DECREASING AIR SPEED AND ENGINE PRESSURE RATIO (EPR) WHICH COULD NOT BE MAINTAINED WITH THE THROTTLE LEVERS AT THE MAXIMUM SETTING.  A STALL WARNING ANNUNCIATION WAS POSTED ON THE PRIMARY FLIGHT DISPLAYS WITH STICK SHAKER ACTIVATED AND THE CREW BEGAN A DESCENT TO 39,000 FT.  AT THAT ALTITUDE, THE ENGINE POWER INDICATIONS RETURNED TO NORMAL ACCOMPANIED WITH HIGHER THAN NORMAL ENGINE VIBRATION (WITHIN ALLOWABLE LIMITS) WHICH REMAINED UNTIL THE A/C DESCE2L72 4F4  FRTT00003NYE00061EN             
20070511000102007051100010GL  2007       5          11         CA070119002      220061019G732323076061        GOVERNOR                                BELL  206   206B        1181511SW  ALLSN 250C  250C20B     03013GL                              POWER TURBINE   FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         DEDESCENT        1                      CA       17                                                             (CAN) THE GOVERNOR WAS INSTALLED WITH ZERO TSN. GROUND RUNS AND RIGGING WERE CARRIED OUT IAW THE MM WITH NO DIFFICULTIES. THE AIRCRAFT WAS FLOWN AND IT WAS NOTICED BY THE PILOT THAT HE WAS ALWAYS CHASING THE N2 TO KEEP IT WITHIN LIMITS (ERRATIC N2 OPS). THE ERRATIC OPS DID NOT IMPROVE AND SEEMED TO WORSEN. THE AIRCRAFT WAS THEN GROUNDED. THE PT GOVERNOR WAS RETURNED FOR WARRANTY.  (TC NR 20070119002)                                                                                                                                                                                                                                                                                                                             1G71 3U3  U  H2SW    E4CE                 
20070511000122007051100012SW  2007       5          11         CA070119006      120061013G2435                SPRING          LUCAS                   BELL  206   206L3       1182108SW  ALLSN 250C  250C30P     03013GL                              STARTER-GEN     BROKEN          W      E   ENGINE SHUTDOWN                                                                                 BH SMOKE/FUMES/ODORS/SPARKS  ELECT. POWER LOSS-50 PC                             TXTAXI/GRND HDL  1                      CA                  1289                                                (CAN) THE STARTER GENERATOR WAS THEN INSTALLED.  UPON FIRST GROUND RUN OF THE AIRCRAFT, SPARKS WERE NOTICED TO BE COMING FROM THE BRUSH AREA. THE AIRCRAFT WAS SHUTDOWN, THE STARTER GENERATOR WAS REMOVED. UPON REMOVAL WE HEARD SOMETHING LOOSE/RATTLING AROUND. WE REMOVED THE BRUSH COVER AND FOUND THAT ONE OF THE SPRINGS WHICH HOLD DOWN THE BRUSHES WAS BROKEN OFF AND RATTLING AROUND CAUSING ARCING. THIS STARTER-GENERATOR WAS RETURNED TO FOR FULL WARRANTY AND A NEW UNIT WAS SENT TO US. (TC NR 20070119006)                                                                                                                                                                                                                      1G71 3U3  U  H2SW    E1GL                 
20070511000142007051100014GL  2007       5          11         CA070119008      220061016G732123070606        FCU                                     BELL  206   206B        1181511SW  ALLSN 250C  250C20B     03013GL                              ENGINE          FAILED          W      E   ENGINE SHUTDOWN                                                                                 F  FLT CONT AFFECTED                                                             TXTAXI/GRND HDL  1                      CA            460                                                       (CAN) THE AIRCRAFT WAS STARTED AND WARMED UP. THE PILOT THEN BEGAN TO SPOOL THE AIRCRAFT UP FROM GROUND IDLE TO FLIGHT IDLE, HOWEVER NOTHING HAPPENED. THIS WAS TRIED A FEW TIMES BUT STILL NO RESPONSE. OTHER TROUBLESHOOTING WAS PERFORMED WITH NO FINDINGS. THE FUEL CONTROL UNIT (FCU) IN QUESTION WAS REMOVED AND AN OVERHAULED UNIT WAS INSTALLED. THE DEFECT WAS RECTIFIED.  (TC NR 20070119008)                                                                                                                                                                                                                                                                                                                                         1G71 3U3  U  H2SW    E4CE                 
20070511000542007051100054NE  2007       5          11         CA070123011      220060112G7261PT6A67D         ENGINE                                  BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE                              NR 1            OIL CONSUMPTION W      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CA       1048810488                         PCEPSO290                   (CAN) CREW NOTED THEIR NR 1 OIL PRESSURE, FLUCTUATING AROUND 75 PSI. THEY RETURNED TO THE GATE AND REPORTED TO MAINTENANCE. INSPECTION OF THE CHIP DETECTOR AND OIL FILTER REVEALED NO FAULTS. THE ENGINE WAS FILLED WITH OIL AND GROUND RUN WITH NO CONSUMPTION OF OIL NOTED.  THE OIL BREATHER LINE WAS BAGGED AND THE A/C RAN FOR 30 MINUTES ON THE GROUND UNDER TARGET TORQUE LOADS AND VERY LITTLE CONSUMPTION WAS NOTED. THE A/C WAS SENT ON AN HOUR LONG TEST FLIGHT WHEN IT RETURNED IT WAS APPROX .5 LITER LOWER ON THE OIL LEVEL. SINCE THE OIL LEVEL WAS STILL AT .75 OF A LITER LOW,  MAINTENANCE LATER DETERMINED THE ENGINE HAD RETURNED TO ITS NORMAL OIL LEVEL. THE A/C WAS FLOWN ON A COUPLE MORE SHORT HOP ROUTS WITH NO OIL U2L72 4T4  TRTA24CE   E26NE                
20070511000722007051100072EA  2007       5          11         CA070126003      220060705G7414BL3493704       MAGNETO                                 BNORM BN2   BN2A        1520204EU  LYC   O540  O540E4C5    41532EA  HARTZLHCC2Y HCC2YK2     GL  ENGINE          LOOSE           W      O   OTHER                                                                                           E  VIBRATION/BUFFET                                                              TXTAXI/GRND HDL  1                      CA       1403                                                           (CAN) ROUGH RUNNING ON RUNUP. FOUND ATTACHMENT FLANGE ON MAGNETO LOOSE. (TC NR 20070126003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1H72 3O3  O  A17EU   E295    5  CP920     
20070511000732007051100073EU  2007       5          11         CA070126004      120060831G79218406E           OIL COOLER                              BNORM BN2   BN2A        1520204EU  LYC   O540  O540E4C5    41532EA  HARTZLHCC2Y HCC2YK2     GL                  CRACKED         W      EA  ENGINE SHUTDOWN         UNSCHED LANDING                                                         KJ FLUID LOSS                WARNING INDICATION                                  CRCRUISE         1                      CA       1400                                                           (CAN) OIL LEAK AROUND CASTING PORT ON THE OIL COOLER ASSEMBLY.  (TC NR 20070126004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1H72 3O3  O  A17EU   E295    5  CP920     
20070511001892007051100189    2007       5          11         CA070129006      420061221G3497                CONNECTOR                               BEECH 76    76          1153005CE  LYC   O360  O360A1G6D        EA  HARTZLHCM2Y HCM2YR      GL  ADF             DISCONNECTED    W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA                                                                      (CAN) ADF INTERMITTENT NDB AND HEADING. AFTER SWAPPING RECEIVERS, ANTENNA, REPLACING ANTENNA TRAY AND CONNECTOR, REPLACING PINS IN RECEIVER TRAY, FOUND CO-AX CONNECTOR INNNER CORE TOUCHING SHIELDING AT RECEIVER TRAY. SNAG ONLY APPREARED WHEN WIRING HARNESS WAS PULLED ON. SOLDERED PORTION OF CONNECTOR HAD WEAKENED OVER TIME AND COULD NO LONGER SUPPORT THE CO-AX WHICH LED TO THE SHORTING. (TC NR 20070129006)                                                                                                                                                                                                                                                                                                                       1L72 3O3  O  A29CE   E286    5  CP43GL    
20070808001342007080800134CE  2007       8          8          CA070131006      120060929G5730                SKIN                                    CESSNA150   152         2071835CE  LYC   O235  O235L2C     41505EA  SNSNCH72C   72CK        EA  WING            CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) 2 CRACKS WERE DETECTED ON THE WING SKIN JUST UNDER THE LEADING EDGE ON BOTH WINGS. THE WING ATTACHMENT FITTINGS OF THE AIRCRAFT WERE INSPECTED AND NO FURTHER CRACKS WERE DISCOVERED.  THE WINGS WERE REMOVED TO CONDUCT A MORE DETAILED EXAMINATION AND THE AMO IS IN CONTACT WITH MFGV FOR REPAIR INSTRUCTIONS. (TC NR 20070131006)                                                                                                                                                                                                                                                                                                                                                                                                     1H71 3O3  ONT3A19    E223    5  NP9045    
20070514000012007051400001NM  2007       5          14         CA070201002      120061218G2821218371          FUEL FILTER                             BOEING767   767300      1385204NM  PWA   R985  R985AN14B   52008NE                                              DIRTY           W      JA  DUMP FUEL               UNSCHED LANDING                                                         J  WARNING INDICATION                                                            CLCLIMB          1                      CA                                                                      (CAN) ON CLIMB (L ENG FUEL FILT) EICAS MSG. RETURNED TO DEPARTURE.  FUEL FILTER INSPECTED AND FOUND DIRTY.  (NO DEBRIS) TECH NOTED NOT TO THE EXTENT THAT WOULD CAUSE THE EICAS INDICATION.  FILTER REINSTALLED. LT ENG DIFFERENTIAL PRESS SW CONX FND CORRODED. CONX CLEANED  NR DIFF PRESS SW REPLACED. CKD SERV ON GRND RUN. REPEAT SNAG ON NEXT T/O. FILTER REPLACED AND CKD SERV ON HIGH PWR GROUND RUN.  (TC NR 20070201002)                                                                                                                                                                                                                                                                                                              2L72 4F3  RRTA1NM    5E1                  
20070514001242007051400124SO  2007       5          14         CA070207004      220060303G8530                VALVE                                   CESSNA150   150H        2071818CE  CONT  O200  O200A       17020SO  MCAULY1A101 1A101DCM    GL  CYLINDER        STUCK           W      O   OTHER                                                                                           R  PARTIAL RPM/PWR LOSS                                                          NRNOT REPORTED   1                      CA       1291                               253128                      (CAN) STUCK VALVE - ENGINE WAS ROUGH RUNNING. FOUND TO BE A STUCK VALVE.  (TC NR 20070207004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3O3  O  3A19    E252    5  NP918     
20070514001262007051400126SO  2007       5          14         CA070207005      220060120G7322                PUMP                                    CESSNA150   150M        2071830CE  CONT  O200  O200A       17020SO  MCAULY1A102 1A102OCM    GL  ACCELERATOR     FAILED          W      O   OTHER                                                                                           Y  ENGINE STOPPAGE                                                               NRNOT REPORTED   1                      CA       5800                                                           (CAN) ON ADDING FULL POWER THE ENGINE STALLED AND STOPPED RUNNING. - FOUND TO BE THE ACCELERATOR PUMP WAS NOT WORKING PROPERLY.  (TC NR 20070207005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H71 3O3  O  3A19    E252    5  NP918     
20070514001282007051400128SO  2007       5          14         CA070207006      120060120G5343                TRUNNION                                PIPER PA34  PA34220T    7103420SO  CONT  O360  TSIO360KB   17025SO  MCAULY3AF32C3AF32C509   GL  NLG             FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) NOSE GEAR TRUNNION DAMAGED AND REPAIRED. (TC NR 20070207006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1L72 3O3  O  A7SO    E9CE    5  CP22EA    
20070514001702007051400170EA  2007       5          14         CA070209006      220061220G7250                TURBINE BLADES                          DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A27      52043EA                              POWER SECTION   FRACTURED       W      O   OTHER                                                                                           X  ENGINE FLAMEOUT                                                               CLCLIMB          1                      CA                                                                      (CAN) DURING CLIMB THE ENGINE EMITTED A LOUD NOISE AND SHUTDOWN UNCOMMANDED.  THE AIRCRAFT DIVERTED TO POINT OF DEPARTURE.  SUBSEQUENT INSPECTION REVEALED FRACTURED POWER TURBINE BLADES.  MFG WILL MONITOR INVESTIGATION OF THE INCIDENT AND ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070209006)                                                                                                                                                                                                                                                                                                                                                                                                                                       1H72 3T4  TRTA9EA    E4EA                 
20070514001712007051400171NE  2007       5          14         CA070209007      220060918G7250                TURBINE BLADES                          AEROSPATR42 ATR42320    8680930EU  PWA   120   PW120            NE                              ENGINE          FRACTURED       W      E   ENGINE SHUTDOWN                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  APAPPROACH       1                      CA                                                                      (CAN) ON APPROACH THE ENGINE FIRE WARNING ACTIVATED, ACCOMPANIED BY AN UNCOMMANDED POWER REDUCTION.  THE CREW DISCHARGED FIRE BOTTLES AND SHUT THE ENGINE DOWN IN FLIGHT.  SUBSEQUENT INVESTIGATION AT MFG REVEALED LPT BLADE FRACTURE IN CREEP. (TC NR 20070209007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2H72 4T4  TRTA53EU   E20NE                
20070515001972007051500197NE  2007       5          15         CA070209018      220061230G7310                PACKING                                 DHAV  DHC8  DHC8301     1386003NM  PWA   PW120 PW123            NE                              FUEL MANIFOLD   LEAKING         W      E   ENGINE SHUTDOWN                                                                                 KRJFLUID LOSS                PARTIAL RPM/PWR LOSS      WARNING INDICATION        CRCRUISE         1                      CA                                                                      (CAN) THE ENGINE LOST POWER IN CRUISE AND WAS SHUT DOWN IN FLIGHT.  SUBSEQUENT INSPECTION FOUND A LEAK AT THE FUEL MANIFOLD TRANSFER TUBES.  ALL TRANSFER TUBE O-RING PACKINGS WERE REPLACED. ON JAN 4TH FUEL LEAKAGE FROM THE SAME TRANSFER TUBES WAS OBSERVED DURING GROUND OPERATIONS.  MFG IS INVESTIGATION PACKING INSTALLATION PROCEDURES AND PROCUREMENT SOURCE AND WILL ADVISE OF ROOT CAUSE ONCE ESTABLISHED. (TC NR 20070209018)                                                                                                                                                                                                                                                                                                      2H72 4T4  TRTA13NM   E20NE                
20070516001722007051600172SW  2007       5          16         CA070216007      120060919G6330206031554003    SPINDLE                                 BELL  206   206B        1181511SW                                                               RT GEARBOX      FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA            1667                                                      (CAN) THE RT TRANSMISSION PYLON SUPPORT SPINDLE FAILED IN-FLIGHT AND AIRCRAFT SUBSEQUENTLY HAD AN UNCONTROLLED COLLISION IN THE WATER.  REFERENCE: TRANSPORT SAFETY BOARD OCCURENCE BULLETIN NR A06P0190 (TC NR 20070216007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1G71 3U      H2SW                         
20070517001302007051700130EU  2007       5          17         CA070221008      120060904G2913350A35109222    PULLEY                                  SNIAS 350   AS350B2     8680813EU  TMECA ARRIELARRIEL1D1        NE                              HYDRAULIC       LOOSE           W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       343                                                            (CAN) HYDRAULIC PULLEY BEARING CONTACT SURFACE WORN CAUSING PULLEY WOBBLE AND LOSS OF BELT TENSION.   (CLICKING) NOISE DURING START UP AND SHUT DOWN, PULLEY AND BEARING REPLACED NEW. (TC NR 20070221008)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3U3  U  H9EU    E19EU                
20070530000222007053000022GL  2007       5          30         CA070226003      320061212G6110HCA3V203        PROPELLER                               STOLAMRC3   RC3         3080203NM  LYC   O480  GO480G1A6   41527EA  HARTZLHCA3V HCA3V203    GL                  CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            304                                       FC33            (CAN) PROP COME IN FOR 10 YEAR OVERHAUL. PIS, CLEAN, NDT, VISUAL INSPECTION, LUB UNSERVICEABLE DUE TO RUST. LINK ARMS P/N 861-3C WORN UNSERVICEABLE, P/N A971 BEARING CORRODED UNSERVICEABLE P/N VL9333C-5 BLADE BORES CORRODED HAD TO BE REAMED AND RE-SHOT PEENED.  THIS PROP NORMALLY WOULD COST APPROXIMATELY  NR 4,500 TO OVERHAUL WITH REPLACED PARTS AND REWORKED BLADE BORES.  THIS OVERHAUL HAS BECOME  NR 14,000. (TC NR 20070226003)                                                                                                                                                                                                                                                                                                 1H71 3O3  ORCA769    E275    5  CP6EA     
20070530000232007053000023SO  2007       5          30         CA070226004      120061220G32104025700         TORQUE LINK                             PIPER PA31  PA31350     7103110SO  LYC   O540  TIO540J2BD  41532EA  HARTZLHCE3Y HCE3YR2A    GL  LT MLG          CRACKED         W      D   RETURN TO BLOCK                                                                                 O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA       11942                                                          (CAN) PILOT NOTICED A VIBRATION ON LT WHEEL. AIRCRAFT RETURNED TO RAMP. LT MAIN LANDING GEAR UPPER TORQUE LINK WAS FOUND CRACKED/BROKEN AT ATTACH LUG. THE TORQUE LINK WAS REPLACED.  (TC NR 20070226004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 3O3  O  A20SO   E14EA   5  CP33EA    
20070530000262007053000026SW  2007       5          30         CA070226007      120061103G3246D2571           SADDLE                                  BELL  212   212         1181420SW  PWA   PT6T  PT6T3B      52045NE                              SKID TUBE       CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) LT SKID SADDLE WAS FOUND CRACKED. (TC NR 20070226007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1G71 4U4  U  H4SW    E22EA                
20070530000342007053000034GL  2007       5          30         CA070227007      220060915G7323                CONTROL LEVER                           BELL  206   206B        1181511SW  ALLSN 250C  250C20B     03013GL                              GOVERNOR        STIFF           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            271                                                       (CAN) THE CONTROL LEVER SHAFT ON THE GOVERNOR WAS FOUND HARD TO MOVE.   SO STIFF THAT THE LINEAR ACTUATOR HAD TO WORK HARD TO MAKE IT TO MOVE. (TC NR 20070227007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1G71 3U3  U  H2SW    E4CE                 
20070530000362007053000036GL  2007       5          30         CA070227009      220060616G7323                CONTROL LEVER                           BELL  206   206B        1181511SW  ALLSN 250C  250C20B     03013GL                              GOVERNOR        STIFF           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            734                                                       (CAN) LEVER CONTROL LEVER HARD TO MOVE ON A FUNCTIONAL CHECK. (TC NR 20070227009)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1G71 3U3  U  H2SW    E4CE                 
20070530000372007053000037GL  2007       5          30         CA070227011      220061023G732323065123        CONTROL LEVER                           BELL  206   206B        1181511SW  ALLSN 250C  250C20B     03013GL                              GOVERNOR        STIFF           W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            152                                                       (CAN) ON A FUCTIONAL CHECK OF THE GOVERNOR CONTROL THERE APPEARED THAT THE CONTROL LEVER ON THE GOVERNOR WAS HARD TO MOVE. THIS WAS CONFIRMED AND THE GOVERNOR WAS REMOVED FOR REPAIR. (TC NR 20070227011)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1G71 3U3  U  H2SW    E4CE                 
20070530000422007053000042SW  2007       5          30         CA070228004      120061016G5302212030132037    SPLICE          BELL                    BELL  212   212         1181420SW  PWA   PT6T  PT6T3       52045EA                              TAILBOOM        CORRODED        W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       10085      ADW03247                                            (CAN) SPLICE CORRODED,TAIL BOOM REPLACED, A/C RETURNED TO SERVICE. (TC NR 20070228004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1G71 4U4  U  H4SW    E22EA                
20070530000432007053000043SW  2007       5          30         CA070228005      120060925G7921R34665          BLADE           BELL                    BELL  205   205A1       1181414SW  LYC   T53   T5313B      41549NE                              BLOWER          MISSING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            434   10880704                                            (CAN) VIBRATION ON OIL COOLER BLOWER, FURTHER INVESTIGATION REVEALED ONE BLADE MISSING. SERVICEABLE OIL COOLER BLOWER INSTALLED, A/C RETURNED TO SERVICE. (TC NR 20070228005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1G71 4U4  U  H1SW    E17EA                
20070524002092007052400209    2007       5          24         CA070302003      420061212G23703LO4534         SWITCH                                  DHAV  DHC6  DHC6300     2802606EA  PWA   PT6   PT6A27      52043EA  HARTZLHCB3T HCB3TN3     GL  VOICE RECORDER  TRIPPED         W      K   NONE                                                                                            L  NO TEST                                                                       ININSP/MAINT     1                      CA                                                                      (CAN) FOLLOWING REMOVAL OF THE CVR FOR TESTING IT WAS DETERMINED THAT THE INERTIA SWITCH HAD BEEN PREVIOUSLY TRIPPED CAUSING THE REQUIRED DATA NOT TO BE RECORDED. A RESET OF THE SWITCH HAD THE SAME RESULTS WITH PREMATURE ACTIVATION CAUSING THE RECORDING TO STOP. THE SWITCH WAS REPLACED WITH A NEW ASSEMBLY. (TC NR 20070302003)                                                                                                                                                                                                                                                                                                                                                                                                         1H72 3T4  TRTA9EA    E4EA    6  CP15EA    
20070613001352007061300135EU  2007       6          13         CA070315006      220061018G7322963178          BOWL                                                                       ROTAX 914   ROTAX914         EU                              CARBURETOR      DISTORTED       W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA       330                                                            (CAN) CARB FLOAT BOWL NUT WAS OVERTORQUED DURING A PREV MAINTENANCE EVENT. THIS DISTORTED THE FLOAT BOWL AND CAUSED THE FLOAT PINS TO BEND OUTWARDS. THIS CAUSED THE FLOATS TO CONTACT THE SIDE OF THE BOWL DURING OPERATION. OPERATOR NOTED INTERMITTENT ROUGH RUNNING THAT WAS ELIMINATED AFTER FLOAT BOWL WAS REPLACED. MM CONTAINS A CONVERSION ERROR THAT INCORRECTLY LISTS THE TORQUE FOR THIS NUT IN FOOT POUND INSTEAD OF INCH POUNDS. THE METRIC TORQUE LISTED IS CORRECT. THIS MM IS CURRENTY BEING REVISED. (TC NR 20070315006)                                                                                                                                                                                                             3  O          EXPE3I               
20070604000352007060400035GL  2007       6          4          CA070322002      120061115G8011656762          GEAR                                    DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO  SNSNCHW69EK W69EK63     EA  STARTER         WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       206                                650200                      (CAN) THE FACT THAT IT IS POSSIBLE TO ACCIDENTALLY ENGAGE THE STARTER DRIVE WHILE THE ENGINE IS RUNNING AND THAT THE STARTER GEAR ENGAGES INTO THE ACCESSORY CASE OF THE ENGINE WHICH WOULD RESULT IN SIMILAR DAMAGE, IT WAS SUSPECTED AT THE TIME THAT THE DAMAGE FOUND WAS A RESULT OF SUCH ENGAGEMENT. THEREFORE AT THE TIME A SDR DID NOT SEEM REQUIRED.   METAL WAS FOUND IN THE OIL FILTER ON INSPECTION, STARTER WAS REMOVED AND BOTH STARTER GEAR AND CLUSTER GEAR WERE FOUND DAMAGED BEYOND MFG LIMITS DESCRIBED IN SB04-7.  FURTHER INSPECTION AT A LATER DATE INDICATED THAT THESE WERE MOST LIKELY NOT DUE TO ACCIDENTAL ENGAGEMENT AS THE DAMAGED AREA ON THE CLUSTER GEAR WAS CONCENTRATED 180 DEGREES APART WHICH WOULD BE CONSIS1L71 3O3  ONTTA4CH   E7SO    5  NTA4CH    
20070604000362007060400036GL  2007       6          4          CA070322003      120061129G55402055450001      BUSHING         DIAMON                  DIAMONDA20  DA20C1      2990001GL  CONT  O240  IO240B      17063SO  SNSNCHW69EK W69EK63     EA  RUDDER          MISSING         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       102                                                            (CAN) DURING INSPECTION IT WAS NOTED THAT THE TOP RUDDER ATTACHMENT PIN BUSHING WAS MISSING. FURTHER INSPECTION REVEALED THE BUSHING HAD FALLEN OUT AND WAS SITTING IN A VOID AREA BELOW THE ASSEMBLY. THE BUSHING WAS RE-INSTALLED IAW MFG INSTRUCTION. THE RUDDER HAD NEVER BEEN REMOVED SINCE MANUFACTURE. (TC NR 20070322003)                                                                                                                                                                                                                                                                                                                                                                                                               1L71 3O3  ONTTA4CH   E7SO    5  NTA4CH    
20070604000512007060400051CE  2007       6          4          CA070327004      120060812G2434DOFF300JR       ALTERNATOR                              CESSNA206   U206G       2073356CE  CONT  O520  IO520F      17032SO  MCAULYD3A34 D3A34C404   GL  ENGINE          FAILED          W      B   EMER. DESCENT                                                                                   HB ELECT. POWER LOSS-50 PC   SMOKE/FUMES/ODORS/SPARKS                            CRCRUISE         1                      CA            300                                                       (CAN) BURNING ELECTRICAL SMELL IN COCKPIT, LOSS OF CHARGING SYSTEM. (TC NR20070327004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3O3  O  A4CE    E5CE    5  CP47GL    
20070604000532007060400053NE  2007       6          4          CA070327007      220060610G8500R985            ENGINE                                  DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE  HAMSTD2D    2D30        NE                  MALFUNCTIONED   W      C   ABORTED TAKEOFF                                                                                 R  PARTIAL RPM/PWR LOSS                                                          TOTAKEOFF        1                      CA                                                                      (CAN) ENGINE NOT PRODUCING FULL TAKEOFF MANIFOLD PRESSURE.  (TC NR 20070327007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1H71 3R3  RRCA806    5E1     5  CP206     
20070503000252007050300025CE  2007       5          3          CA070402005      120060102G32469543991         WHEEL                                   LEAR  35    35A         5170602CE  GARRTTTFE731TFE73122B   01518WP                              NR 3            WRONG PART      W      K   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      CA            147                                                       (CAN) DURING ROUTINE PRE-FLIGHT INSPECTION, NR 3 MAIN WHEEL ASSY FOUND TO BE ASSEMBLED INCORRECTLY. WHEEL HALF`S WERE MISALIGNED BY ONE BOLT HOLE. AMM 32-A2-00 PG.210. FORGED NRS AND LOT NRS WERE NOT ALIGNED. MAIN WHEEL ASSEMBLY REMOVED FROM AIRCRAFT, REPAIRED AND RE-ASSEMBLED IAW AMM 32-42-00 AND CMM AP-480 32-40-35. (TC NR 20070402005)                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F4  F  A10CE   E6WE                 
20070503000282007050300028GL  2007       5          3          CA070402007      120060710G3246C2UF2291        MECHANISM       EDOFLOATS               DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE  HARTZLHCB3R HCB3R304    GL  FLOAT WIRE PULL WRONG PART      W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                  489                                                 (CAN) FORWARD RT WIRE PULL BROKE, NEW WIRE PULL P/N C2UF2291 FOUND TO BE TOO SHORT. INVESTIGATION REVEALED WRONG TIE RODS AND WIRE PULLS INSTALLED IAW APPROVED DRAWINGS ACCEPTED REPLACEMENT PARTS INSTALLED IAW APPROVED DRAWINGS. (TC NR 20070402007)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1H71 3R3  RRCA806    5E1     5  CP28EA    
20070504001052007050400105NM  2007       5          4          CA070404005      120060426G5697                TERMINAL BLOCK  BOEING                  BOEING757   75728A      1384976NM  RROYCERB211 RB211535E4  54555NE                              WINDOW          OVERHEATED      W      A   UNSCHED LANDING                                                                                 B  SMOKE/FUMES/ODORS/SPARKS                                                      CRCRUISE         1                      CA                  0525141740                                          (CAN) UNKNOWN ODOR IN CONTROL CABIN THOUGHT TO BE FROM LAVATORY. ISOLATED TO FLIGHT DECK. ON DESCENT INTO AIRPORT, ODOR DISSIPATED AND FAULT COULD NOT BE FOUND. AIRCRAFT CONTINUED WITH NO FUMES BUT SLIGHT ODOR WAS PRESENT AT END OF FLIGHT. TERMINAL BLOCK ON SLIDING WINDOW WAS FOUND OVERHEATED.  WINDOW WAS REPLACED. (TC NR 20070404005)                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F4  FRTA2NM    E12EU                
20070808001602007080800160CE  2007       8          8          CA070502013      120060603G2720051010551       CONTROL CABLE                           CESSNA185   185A        2072804CE  CONT  O520  IO520D      17032SO  MCAULY2A34C D2A34C58    GL  RUDDER CONTROL  BROKEN          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA                                                                      (CAN) THE BOLT THAT ATTACHES THE LT FORWARD RUDDER CABLE TO THE RUDDER PEDAL SETUP WAS ORIGINALLY TOO TIGHTLY DONE UP. THE CABLE ATTACHMENT FORK WAS NOT ABLE TO MOVE FREELY ON END, IN THE FORK, AND BREAK UNDER LOAD.  (TC NR 20070502013)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H71 3O3  O  3A24    E5CE    5  CP3EA     
20070809000372007080900037CE  2007       8          9          CA070517003      120061214G27010411257         CONTROL WHEEL                           CESSNA172   172P        2072436CE  LYC   O320  O320D2J     41508EA                              COCKPIT         FAILED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) EXCESSIVE PLAY IN (U) JOINT ON LT CONTROL WHEEL. (TC NR 20070517003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1H71 3O3  ONT3A12    E274                 
20080319001382008031900138CE  2008       3          19         CA070517004      120060918G3710211CW           PUMP                                    CESSNA172   172P        2072436CE  LYC   O320  O320D2J     41508EA                              VACUUM SYS      FAILED          W      E   ENGINE SHUTDOWN                                                                                 O  OTHER                                                                         TXTAXI/GRND HDL  1                      CA            629                                                       (CAN) LOSS OF VACUUM DURING START-UP. (TC NR 20070517004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H71 3O3  ONT3A12    E274                 
20070618001602007061800160EA  2007       6          18         CA070517005      220061203G7414                COIL                                    CESSNA172   172M        2072418CE  LYC   O320  O320E2D     41508EA                              MAGNETO         BURNED          W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            1785                                                      (CAN) RT MAGNETO DEAD ON RUN-UP. (TC NR 20070517005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H71 3O3  ONT3A12    E274                 
20070618001612007061800161EA  2007       6          18         CA070517006      220061125G8500                ENGINE                                  CESSNA172   172M        2072418CE  LYC   O320  O320E2D     41508EA                                              SMOKE           W      FE  ACTIVATE FIRE EXT.      ENGINE SHUTDOWN                                                         B  SMOKE/FUMES/ODORS/SPARKS                                                      NRNOT REPORTED   1                      CA                                          17262921                    (CAN) SMOKE SEEN COMING FROM COWLS INDUCTION FIRE SUSPECTED, SHUTDOWN AND PILOT DISCHARGED FIRE EXTINGUISHER INTO COWLING.  (TC NR 20070517006)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 1H71 3O3  ONT3A12    E274                 
20070820001112007082000111SO  2007       8          20         CA070716004      220060511G8530AEC631397       CYLINDER                                CESSNA185   A185E       2072818CE  CONT  O520  IO520D      17032SO  HARTZLHCC3Y HCC3YF1     GL  NR 4            CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) NR 4 CYLINDER FOUND CRACKED DURING INSPECTION (TC IN20070716004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1H71 3O3  O  3A24    E5CE    5  CP25EA    
20070820001382007082000138EA  2007       8          20         CA070720009      120060727G56106003303025      WINDSHIELD                              CNDAIRCL601 CL6012A12   1900303EA  GE    CF34  CF348E5A1   30015NE                              COCKPIT         CRACKED         W      O   OTHER                                                                                           O  OTHER                                                                         CRCRUISE         1                      CA       1233                                                           (CAN) LT WINDSHIELD OUTER PANE CRACKED IN FLIGHT WITH NO LOSS OF PRESSURIZATION.  FLIGHT CONTINUED NORMALLY.  NEW WINDSHIELD INSTALLED AND AIRCRAFT RETURNED TO SERVICE. (TC NR 20070720009)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2L72 4F4  FRTA21AE   E00063EN             
             20081104     CE  2008       11         4          CA070726005      120061230G8011EBB75A          GEAR                        MZ4206      CESSNA172   172K        2072430CE  LYC   O320  O320E2D     41508EA  MCAULY1C160 1C160DTM    GL  STARTER         FAILED          W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       241                                                            (CAN) ENGINE WOULD NOT START, STARTER REMOVED, BENDIX FOUND SHATTERED. (TC NR 20070726005)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1H71 3O3  ONT3A12    E274    5  NP910     
20070820001622007082000162GL  2007       8          20         CA070731003      120060929G5540C2CF17778       TORQUE TUBE                             DHAV  DHC2  DHC2MKI     2801830GL  PWA   R985  R985AN14B   52008NE  HAMSTD2D    2D30        NE  RUDDER          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) CRACK ON RUDDER TORQUE TUBE RT SIDE OB. (TC NR 20070731003)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1H71 3R3  RRCA806    5E1     5  CP206     
20070820001632007082000163CE  2007       8          20         CA070731004      120061023G272007123094        BELLCRANK                               CESSNA185   A185E       2072818CE  CONT  O520  IO520D      17032SO  MCAULY2A34C D2A34C58    GL  RUDDER          CRACKED         W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) BELLCRANK HAS CRACKS ADJACENT TO AN3 BOLT HOLES.  (TC NR 20070731004)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1H71 3O3  O  3A24    E5CE    5  CP3EA     
20080131000502008013100050    2008       1          31         CA071018002      420061113G2562AK450           ELT                                     ROBSINR22   R22BETA     7640110NM  LYC   O360  O360J2A     41514EA                              CABIN           FAILED          W      K   NONE                                                                                            L  NO TEST                                                                       ININSP/MAINT     1                      CA                                                                      (CAN) SENT 2 ELTS TO INLAND COMMUNICATIONS FOR SERVICING, BOTH ELTS HAD FAULTY G-SWITCHES AND COULD NOT BE REPAIRED. SENT CORE IN FOR NEW AK-450 S/N 485068 THAT WAS INSTALLED ON NOV 13/06, WENT OFF ON LANDING AND AGAIN IN FLIGHT. REMOVED ELT ON HOV 14/06. INSTALLED NEW AK-450-1 ELT S/N 485603 JAN 11/07, FAILED ON MAR 4/07 AND REMOVED. INSTALLED ANOTHER NEW AK-450-1 ELT S/N 484979 ON MAY 30/07 AND IS STILL SERVICE. (TC NR 20071018002)                                                                                                                                                                                                                                                                                           1G71 3O3  O  H10WE   E286                 
20080225000842008022500084NE  2008       2          25         CA071207001      320061005G61116903A10         BLADE           HAMSTD                  CNDAIRCL215 CL2151A10   1900320EA  PWA   R1340 CWASP       52016NE  HAMSTD43E   43E60       NE  PROPELLER       UNSERVICEABLE   W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA            405   N196694                                             (CAN) DURING INSPECTION IAW AD 81-13-06R2 AND S/B 664, A CRACK WAS FOUND EMINATING FROM THE BLADE BUSHING SCREW HOLE. CRACK WAS FOUND TO BE TOO LARGE TO BE REMOVED. BLADE WAS RENDERED UNSERVICEABLE. BLADE S/N 852006. (TC NR 20071207001)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2H72 4R3  RRTA14EA   ATC14   6  CP871     
20080225000882008022500088SW  2008       2          25         CA071210002      120061227G6330204031927005    MOUNT                                   BELL  205   205A1       1181414SW  LYC   T53   T5317BLYC   41616NE                              TRANSMISSION    SHEARED         W      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      CA       775        A124043                                             (CAN) DURING ROUTINE POST FLIGHT DAILY INSP, (3) OF THE (4) AN4H6A BOLTS THAT ATTACH THE TRANSMISSION AFT (5TH) MOUNT TO THE AIRFRAME FITTING ASSY WERE FOUND SHEARED OFF. FLIGHT OPERATION WERE NOT AFFECTED AND CONSIDERED TO BE NORMAL AT THE TIME. THE MOUNT AND FITTING WERE REMOVED, INSPECTED AND THE AIRCRAFT RETURNED TO SERVICE. (TC NR 20071210002)                                                                                                                                                                                                                                                                                                                                                                                  1G71 4U4  U  H1SW    E17EA                
20080225001002008022500100NE  2008       2          25         CA071212001      220061227G7200                ENGINE                                  AMD   FALC50FALCON50MYST2730106EU  GARRTTTFE731TFE73140    29001NE                              NR 2            MAKING METAL    W      E   ENGINE SHUTDOWN                                                                                 KMJFLUID LOSS                OVER TEMP                 WARNING INDICATION        NRNOT REPORTED   1                      CA                                          P115243                     (CAN) ON DESERT TO BASE CREW NOTICED NR 2 ENGINE OIL PRESSURE AND TEMPERATURE CLIMBING, POWER REDUCED TO IDLE. OIL PRESSURE DROPPED TO BELOW MINIMUMS (IN YELLOW ARC). CREW PERFORMED PRECAUTIONARY SHUTDOWN AND LANDED NORMALLY.   SUBSEQUENT INVESTIGATION REVEALED OIL HAD VENTED OUT THROUGH BREATHER. CHIP DETECTOR AND GEARBOXES CONTAMINATED WITH METAL PARTICLES. ENGINE RETURNED FOR REPAIR AND INVESTIGATION OF CAUSE. (TC NR 20071212001)                                                                                                                                                                                                                                                                                            2L73 4F4  F  A46EU   E1NM                 
20080225001162008022500116EU  2008       2          25         CA071212015      120061123G28222260961         PUMP                                    BAG   JETSTMJETSTM3212  1500217EU  GARRTTTPE331TPE33112UHR      WP  ROTOL R333  R333482F12  GL  FUEL BOOST      FAILED          W      O   OTHER                                                                                           J  WARNING INDICATION                                                            CRCRUISE         1                      CA                                                                      (CAN) RT FUEL BOOST PUMP FAILED. (TC NR 20071212015)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4T4  TRTBA15CAA E4WE    6  CP61GL    
20080220000452008022000045NM  2008       2          20         CA080123009      120061218G291082590010239     LINE                                    DHAV  DHC8  DHC8103     1386005NM  PWA   120   PW120A           NE  HAMSTD14SF  14SF7       NE  HYDRAULIC SYS   LEAKING         W      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      CA       43213                                                          (CAN) LEAK FROM PIN HOLE IN HYD LINE RT WING, ON GROUND PRIOR TO TAXI TO GATE A/C GROUNDED. HYD LINE ASSY FOR RT WING SPOILERS REPLACED WITH NO FURTHER INCIDENT OR LEAKAGE. (TC NR 20080123009)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2H72 4T4  TRTA13NM   E20NE   6  CP7NE     
             20081107     SO  2008       11         7          CA080717004      120060517G2435                FRICTION DISC                           PIPER PA31  PA31        7103102SO  LYC   O540  TIO540A2C   41532EA                              STARTER GEN     WORN            W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA                                                                      (CAN) GENERATOR FRICTION DISC WAS WORN OUT AND WAS ALLOWING THE STARTER GENERATOR SHAFT TO WHIP ABOUT 6000 RPM (OPERATING RANGE)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L72 3O3  O  A20SO   E14EA                
             20081107     EA  2008       11         7          CA080915001      120060802G2820G201G202        FITTING                                 FOUND FBA   FBA2C1      3640103EA  LYC   O540  IO540AE1A5  41530NE                              FUEL SYSTEM     UNDERTORQUED    W      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CA       532                                                            (CAN) FOUND NUMEROUS FUEL FITTINGS WHICH CONNECT THE FUEL LINES TO THE HEADER TANKS TO BE SEEPING FUEL. APPROXIMATE TIME OF SERVICE 532 HRS. PIPE THREAD FITTINGS HAD NO THREAD LUBE/SEALANT. THE VENDOR NOTED THAT THE FUEL FITTINGS WERE NOT PROPERLY TORQUED. THIS MAY REPRESENT A QUALITY CONTROL ISSUE AT THE FOUND ACFT PRODUCTION FACILITY. AT PRESENT THE USDOI, AVIATION MANAGEMENT DIRECTORATE, IS INVESTIGATING THIS EVENT WITHIN ITS FLEET."                                                                                                                                                                                                                                                                                        1H71 3O3  ONCA7EA    1E4                  
20060705000122006070500012NE  2006       7          5          CHI2852          220060419G72502002T29P01      LOCK NUT        GE                      BOEING107   1072        9420604EA  GE    CT58  CT581401    30011NE                              PWR TURBINE     FAILED          B  CHIRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM096672D           52          2           280102L                     UPON RECEIPT OF ENGINE FOR MAINTENANCE, IT WAS DISCOVERED THAT THE POWER TURBINE LOCKNUT HAD LOST TORQUE AND BACKED OFF OF THE POWER TURBINE TIE BOLT.  THE PROBABLE CAUSE WAS LOSS OF TORQUE.  A SPECIAL INSPECTION WAS INITIATED TO INCLUDE INSPECTING RUN-ON TORQUE.  A SPECIAL INSPECTION WAS INITIATED TO INCLUDE INSPECTING RUN-ON TORQUE AND PERFORMING AN NDT INSP OF ALL LOCKNUTS IN INVENTORY AND THOSE UNDERGOING MAINT.  ALL LOCKNUTS CURRENTLY INSTALLED ON AC WILL BE REPLACED AND THOSE LOCKNUTS WILL BE RETURNED TO REPAIR STA FOR INSP.  MFG WILL BE NOTIFIED OF INCIDENT IMMEDIATELAY.  (K)                                                                                                                                   2G72 4U4  U  1H16    1E3                  
20060705000092006070500009EA  2006       7          5          CHI44188         120060518G6300107D25535       COVER                                   BOEING107   1072        9420604EA                                                               MIXER BOX       CRACKED         B  CHIRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM09194CH858                    404                                     CRACK DISCOVERED IN THE MIX BOX COVER, PN 107D25535.  THE CRACK RUNS FROM JUST UNDER THE WEB ON THE TOP OF THE MIX BOX LT SIDE, INTO THE O-RING GROOVE IN THE FRONT OF THE COVER.  CRACK IS APPROX 6 INCHES OVERALL IN LENGTH.  DAMAGED AREA OF THE COVER HAS BEEN SENT TO LABORATORY FOR ANALYSIS.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                        2G72 4U      1H16                         
20060706001032006070600103EA  2006       7          6          CHIR823CA        120060608G6410114R170244      BLADE                                   BOEING234   234         1385049EA                                                               TAIL ROTOR      DEBONDED        C  CHIRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM09CFHFB21142                  MJ005                                   ROTOR BLADE HAD A LARGE SKIN DEBOND ON THE LOWER SURFACE FROM THE TRIM TAB OB, BETWEEN STA 227 AND STA 329 APPROXIMATELY 475-500 SQ INCHES (ALLOWABLE REPAIR LIMITS ARE 20 INCHES SPAN WISE AND 13 INCHES CHORD WISE.  UNBONDED SKIN WAS REMOVED TO EXPOSE HONEYCOMB CORE FOR INSPECTION.  HONEYCOMB WAS OIL FREE AND APPEARED TO BE IN GOOD CONDITION.  THE ROTOR BLADE WILL UNDERGO FURTHER INVESTIGATION TO DETERMINE THE PROBABLE CAUSE AND REPAIR SCHEME, IF POSSIBLE.  MFG HAS BEEN NOTIFIED.  (K)                                                                                                                                                                                                                                        2G72 4U      H9EA                         
20060321000582006032100058    2006       3          21         CMRR200602002    420060227G31607018704902      POWER SUPPLY    HONEYWELL   DU870       DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              EFIS            OVERTEMP        B  CMRRK   NONE                                                                                            MH OVER TEMP                 ELECT. POWER LOSS-50 PC                             ININSP/MAINT     1                      SO13406FJ9042       00046519    3156                                    THE HONEYWELL DU-870 DISPLAY UNIT REFERENCED HEREIN FAILED JUST PRIOR TO TAKEOFF.  THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                               2H72 4T4  FRTA55NM   E35NE                
20060316000402006031600040    2006       3          16         CMRR200602003    420060222G31607018704902      POWER SUPPLY    HONEYWELL   DU870       DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              COCKPIT         OVERTEMP        B  CMRRK   NONE                                                                                            HM ELECT. POWER LOSS-50 PC   OVER TEMP                                           ININSP/MAINT     1                      SO13406FJ9042       99095560    3156                                    +THE NR 1 PFD DU-870 DISPLAY UNIT REFERENCED HERE IN FAILED DURING GROUND OPERATIONS. THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY PN 7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                             2H72 4T4  FRTA55NM   E35NE                
20060322000492006032200049    2006       3          22         CMRR200603004    420060314G31607018704902      POWER SUPPLY    HONEYWELL   DU870       DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              EFIS            OVERTEMP        B  CMRRK   NONE                                                                                            MH OVER TEMP                 ELECT. POWER LOSS-50 PC                             ININSP/MAINT     1                      SO13423FJ7360       00107696    3181                                    THE NR 1 PFD HONEYWELL DU-870 DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS.  THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                   2H72 4T4  FRTA55NM   E35NE                
20060321000672006032100067    2006       3          21         CMRR200603005    420060314G31607018704902      POWER SUPPLY    HONEYWELL   DU870       DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              EFIS            OVERTEMP        B  CMRRK   NONE                                                                                            MH OVER TEMP                 ELECT. POWER LOSS-50 PC                             ININSP/MAINT     1                      SO13423FJ7360       00107818    3181                                    THE NR 2 MFD HONEYWELL DU-870 DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS PRIOR TO FERRY.  THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                    2H72 4T4  FRTA55NM   E35NE                
20060321000492006032100049    2006       3          21         CMRR200603006    420060314G31607018704902      POWER SUPPLY    HONEYWELL   DU870       DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              EFIS            OVERTEMP        B  CMRRK   NONE                                                                                            MH OVER TEMP                 ELECT. POWER LOSS-50 PC                             ININSP/MAINT     1                      SO13423FJ7360       00107817    3181                                    THE NR 1 MFD HONEYWELL DU-870 DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS PRIOR TO FERRY.  THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                    2H72 4T4  FRTA55NM   E35NE                
20060321001202006032100120    2006       3          21         CMRR200603007    420060314G31607018704902      POWER SUPPLY    HONEYWELL   DU870       DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              EFIS            OVERTEMP        B  CMRRK   NONE                                                                                            MH OVER TEMP                 ELECT. POWER LOSS-50 PC                             ININSP/MAINT     1                      SO13423FJ7360       00107359    3181                                    THE NR 2 PFD HONEYWELL DU-870 DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS PRIOR TO FERRY.  THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                    2H72 4T4  FRTA55NM   E35NE                
20060321001812006032100181    2006       3          21         CMRR200603008    420060314G31607018704902      POWER SUPPLY    HONEYWELL   DU870       DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              EFIS            OVERTEMP        B  CMRRK   NONE                                                                                            MH OVER TEMP                 ELECT. POWER LOSS-50 PC                             ININSP/MAINT     1                      SO13423FJ7360       00036246    3181                                    THE EICAS HONEYWELL DU-870 DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS PRIOR TO FERRY.  THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                       2H72 4T4  FRTA55NM   E35NE                
20060427001332006042700133    2006       4          27         CMRR200603009    420060324G31607018704902      POWER SUPPLY    HONEYWELL   DU870       DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              DISPLAY UNIT    FAILED          B  CMRRK   NONE                                                                                            O  OTHER                                                                         TXTAXI/GRND HDL  1                      SO13423FJ7360       0201A741    3181                                    THE EICAS HONEYWELL DU-870 DISPLAY UNIT REFERENCED HEREIN FAILED DURING TAXI PRIOR TO FERRY.  THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT PN:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT. THIS PARTICULAR DU POSITION WAS PREVIOUSLY REPLACED AS WELL ON 3-14-06 BUT THE CUSTOMER DID NOT WANT AN UPGRADED MOD K UNIT INSTALLED.  FURTHER INSPECTIONS WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE.                                                                                                                                                                                                                                                                                        2H72 4T4  FRTA55NM   E35NE                
20060510002242006051000224    2006       5          10         CMRR200604010    420060426G31607018704902      POWER SUPPLY    HONEYWELL   DU870       DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              DISPLAY UNIT    FAILED          B  CMRRK   NONE                                                                                            O  OTHER                                                                         TXTAXI/GRND HDL  1                      SO13407FJ8913       00046519    3157                                    THE NR 1 PFD DISPLAY UNIT REFERENCED HERE IN FAILED DURING TAXI OPERATIONS PRIOR TO FLIGHT. THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT PN:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT. FURTHER INSPECTIONS WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                  2H72 4T4  FRTA55NM   E35NE                
20060510002252006051000225    2006       5          10         CMRR200604011    420060426G31607018704902      POWER SUPPLY    HONEYWELL   DU870       DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              DISPLAY UNIT    FAILED          B  CMRRK   NONE                                                                                            O  OTHER                                                                         TXTAXI/GRND HDL  1                      SO13407FJ8913       00036262    3157                                    THE NR 1 MFD DISPLAY UNIT REFERENCED HERE IN FAILED DURING TAXI OPERATIONS PRIOR TO FLIGHT. THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT PN:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTIONS WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                 2H72 4T4  FRTA55NM   E35NE                
20060619001772006061900177    2006       6          19         CMRR200606012    420060526G31607018704902      POWER SUPPLY    HONEYWELL   DU870       DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              EFIS            FAILED          B  CMRRK   NONE                                                                                            MH OVER TEMP                 ELECT. POWER LOSS-50 PC                             ININSP/MAINT     1                      SO13403FJ9553       00036143    3149                                    THE NR 1 MFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS PRIOR TO FLIGHT. THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT PN: 7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT. FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                 2H72 4T4  FRTA55NM   E35NE                
20060620000192006062000019    2006       6          20         CMRR200606013    420060526G31607018704902      POWER SUPPLY    HONEYWELL   DU870       DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              DISPLAY         FAILED          B  CMRRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO13403FJ9553       00087125    3149                                    THE NR 1 PFD HONEYWELL DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS PRIOR TO FLIGHT.  THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT PN:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF DU FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                      2H72 4T4  FRTA55NM   E35NE                
20061031001282006103100128    2006       10         31         CMRR200610014    420061027G31607018704902      POWER SUPPLY    HONEYWELL   DU870       DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              EFIS            FAILED          B  CMRRK   NONE                                                                                            H  ELECT. POWER LOSS-50 PC                                                       ININSP/MAINT     1                      SO13428FJ6881       01028536    3193                                    THE NR 1 PFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS.  THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                           2H72 4T4  FRTA55NM   E35NE                
20061031001292006103100129    2006       10         31         CMRR200610015    420061027G31607018704902      POWER SUPPLY    HONEYWELL   DU870       DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              EFIS            FAILED          B  CMRRK   NONE                                                                                            H  ELECT. POWER LOSS-50 PC                                                       ININSP/MAINT     1                      SO13428FJ6881       01059291    3193                                    THE NR 2 MFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS.  THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                           2H72 4T4  FRTA55NM   E35NE                
20061031001302006103100130    2006       10         31         CMRR200610016    420061027G31607018704902      POWER SUPPLY    HONEYWELL   DU870       DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              EFIS            FAILED          B  CMRRK   NONE                                                                                            H  ELECT. POWER LOSS-50 PC                                                       ININSP/MAINT     1                      SO13428FJ6881       01018337    3193                                    THE EICAS DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS.  THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                              2H72 4T4  FRTA55NM   E35NE                
20061031001312006103100131    2006       10         31         CMRR200610017    420061027G31607018704902      POWER SUPPLY    HONEYWELL   DU870       DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              EFIS            FAILED          B  CMRRK   NONE                                                                                            H  ELECT. POWER LOSS-50 PC                                                       ININSP/MAINT     1                      SO13428FJ6881       00097242    3193                                    THE NR 4 MFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS.  THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                           2H72 4T4  FRTA55NM   E35NE                
20061031001322006103100132    2006       10         31         CMRR200610018    420061027G31607018704902      POWER SUPPLY    HONEYWELL   DU870       DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              EFIS            FAILED          B  CMRRK   NONE                                                                                            H  ELECT. POWER LOSS-50 PC                                                       ININSP/MAINT     1                      SO13428FJ6881       00097260    3193                                    THE NR 5 PFD DISPLAY UNIT REFRENCED HEREIN FAILED DURING GROUND OPERATIONS.  THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                            2H72 4T4  FRTA55NM   E35NE                
20061031001332006103100133    2006       10         31         CMRR200610019    420061019G31607018704902      POWER SUPPLY    HONEYWELL   DU870       DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              EFIS            FAILED          B  CMRRK   NONE                                                                                            H  ELECT. POWER LOSS-50 PC                                                       ININSP/MAINT     1                      SO13405FJ9298       00036374    3155                                    THE EICAS DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS.  THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                              2H72 4T4  FRTA55NM   E35NE                
20061031001342006103100134    2006       10         31         CMRR200610020    420061023G31607018704902      POWER SUPPLY    HONEYWELL   DU870       DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              EFIS            FAILED          B  CMRRK   NONE                                                                                            H  ELECT. POWER LOSS-50 PC                                                       ININSP/MAINT     1                      SO13420FJ8290       00046474    3178                                    THE NR 5 PFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS.  THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                           2H72 4T4  FRTA55NM   E35NE                
20061031001352006103100135    2006       10         31         CMRR200610021    420061023G31607018704902      POWER SUPPLY    HONEYWELL   DU870       DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              EFIS            FAILED          B  CMRRK   NONE                                                                                            H  ELECT. POWER LOSS-50 PC                                                       ININSP/MAINT     1                      SO13420FJ8290       00107614    3178                                    THE NR 1 PFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS.  THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                           2H72 4T4  FRTA55NM   E35NE                
20061031001362006103100136    2006       10         31         CMRR200610022    420061019G31607018704902      POWER SUPPLY    HONEYWELL   DU870       DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              EFIS            FAILED          B  CMRRK   NONE                                                                                            H  ELECT. POWER LOSS-50 PC                                                       ININSP/MAINT     1                      SO13405FJ9298       00067009    3155                                    THE NR 2 MFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS.  THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                           2H72 4T4  FRTA55NM   E35NE                
20061031001372006103100137    2006       10         31         CMRR200610023    420061023G31607018704902      POWER SUPPLY    HONEYWELL   DU870       DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              EFIS            FAILED          B  CMRRK   NONE                                                                                            H  ELECT. POWER LOSS-50 PC                                                       ININSP/MAINT     1                      SO13420FJ8290       02014704    3178                                    THE NR 4 MFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS.  THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                           2H72 4T4  FRTA55NM   E35NE                
20061101001122006110100112    2006       11         1          CMRR200611024    420061017G31607018704902      POWER SUPPLY    HONEYWELL   DU870       DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              EFIS            FAILED          B  CMRRK   NONE                                                                                            H  ELECT. POWER LOSS-50 PC                                                       ININSP/MAINT     1                      SO13365SK8912       00066818    3165                                    THE NR 1 PFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS.  THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                           2H72 4T4  FRTA55NM   E35NE                
20061101001112006110100111    2006       11         1          CMRR200611025    420061017G31607018704902      POWER SUPPLY    HONEYWELL   DU870       DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              EFIS            FAILED          B  CMRRK   NONE                                                                                            H  ELECT. POWER LOSS-50 PC                                                       ININSP/MAINT     1                      SO13365SK8912       00066839    3165                                    THE EICAS DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS.  THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT P/N:7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                              2H72 4T4  FRTA55NM   E35NE                
20061101001152006110100115    2006       11         1          CMRR200611026    420061017G31607018704902      POWER SUPPLY    HONEYWELL   DU870       DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              EFIS            FAILED          B  CMRRK   NONE                                                                                            H  ELECT. POWER LOSS-50 PC                                                       ININSP/MAINT     1                      SO13365SK8912       00066873    3165                                    THE NR 2 MFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS.  THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT P/N 7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                           2H72 4T4  FRTA55NM   E35NE                
20061101001142006110100114    2006       11         1          CMRR200611027    420061017G31607018704902      POWER SUPPLY    HONEYWELL   DU870       DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              EFIS            FAILED          B  CMRRK   NONE                                                                                            H  ELECT. POWER LOSS-50 PC                                                       ININSP/MAINT     1                      SO13365SK8912       00128053    3165                                    THE NR 5 PFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS.  THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT P/N 7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                           2H72 4T4  FRTA55NM   E35NE                
20061101001132006110100113    2006       11         1          CMRR200611028    420061017G31607018704902      POWER SUPPLY    HONEYWELL   DU870       DORNERDO32  DO328300           NM  PWA   306   PW306B           NE                              EFIS            FAILED          B  CMRRK   NONE                                                                                            H  ELECT. POWER LOSS-50 PC                                                       ININSP/MAINT     1                      SO13365SK8912       00066838    3165                                    THE NR 4 MFD DISPLAY UNIT REFERENCED HEREIN FAILED DURING GROUND OPERATIONS.  THE SUSPECTED SPECIFIC COMPONENT FAILURE IS THE HIGH VOLTAGE POWER SUPPLY UNIT P/N 7018704-902 INSTALLED INSIDE THE CRT DISPLAY UNIT.  FURTHER INSPECTION WILL BE REQUIRED TO VERIFY THE EXACT CAUSE OF THE DU FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                           2H72 4T4  FRTA55NM   E35NE                
20070104000232007010400023NM  2007       1          4          COOSDR060032     120060824G5712                RIB                                     BOEING737   737301      1384611NM  GE    CFM56 CFM56*      13802NE                              RT WING         CRACKED         B  EE4YK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO23563AU                       23551                                   RT WING AT WBL 114 RIB UPPER CHORD CRACKED NEAR STR-2.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA16WE   E2GL                 
20070104000242007010400024NM  2007       1          4          COOSDR060034     120060825G3320S283U00816      BALLAST                                 BOEING737   7377Q8      1384418NM  CFMINTCFM56 CFM563B2    13802EU                              CABIN           OVERHEATED      B  EE4YO   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      NRNOT REPORTED   1                      SO23161LF                       28224                                   PAX CABIN LIGHT BALLAST OVERHEATED BURNING INSULATION BLANKET AT BS 328, STR 1.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F4  FRTA16WE   E21EU                
20070125000202007012500020CE  2007       1          25         CWQD200701       120061225G2910AE1011888G0106  HOSE                                    CESSNA750   750         2076810CE  ALLSN AE3007AE3007C          GL                              HYD SYSTEM      LEAKING         E  DXTAO   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  APAPPROACH       1                      GL05990QS4918                   7500190                                 DURING FINAL APPROACH THE GEAR WAS SELECTED DOWN AND THE (A) HYDRAULIC QTY FELL TO 6 PERCENT WITH (HYD VOL LOW) CAS MESSAGE.  JACKED AIRCRAFT, REMOVED PANEL 184DB AND FOUND THE RT GEAR MLG ACTUATOR RETRACT HOSE ASSY HAD A HOLE IN IT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4J4  FRTT00007WITE6CH                
20060405000022006040500002CE  2006       4          5          CWQR2006001      120060302G2710666000216       TURNBUCKLE                              CESSNA560   560XL       2076702CE                                                               CONTROL CABLE   MISMANUFACTURED B  DXTAK   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      GL05631QS                       5605131                                 DURING A CABLE CHANGE ON THE AILERON SYSTEM, THE PROPER CABLE TENSION COULD NOT BE BROUGHT UP.  UPON INSPECTION FOUND NEW CABLE ASSEMBLY TERMINAL END WAS NOT PROPERLY MACHINED.  BECAUSE THE NECK (AREA BETWEEN THREADS AND TOOL HOLE) WAS NOT REDUCED THE TURNBARREL BOTTOMS ON THREADS AND CAN NOT BE ADJUSTED TO TENSION REQUIRED.                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA22CE                        
20060405000362006040500036CE  2006       4          5          CWQR2006002      120060302G5100991406742       OXYGEN BOTTLE                           CESSNA750   750         2076810CE                                                                               UNSERVICEABLE   B  DXTAO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL05942QS                       7500024                                 RECEIVED OXYGEN CYLINDER AND REGULATOR FROM CESSNA WITH A CYLINDER BEYOND ITS SERVICE LIFE.  BOTTLE HAS 15 YEAR SERVICE LIFE PER CE750 M/M CHAP 5. BOTTLE MFD DATE 9/87.  RED TAGGED BOTTLE AND RETURNED TO CESSNA PARTS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4J    RTT00007WI                     
20060501002392006050100239CE  2006       5          1          CWQR2006003      120060308G341168C48           DRAIN VALVE                             CESSNA560   560XL       2076702CE                                                               PITOT STATIC SYSLOOSE           B  DXTAK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05633QS                       5605526                                 FOUND THE STATIC SYSTEM DRAIN VALVE POPPET RETAING RING COMING LOOSE FROM VALVE BASE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F    RTA22CE                        
20060411000482006041100048CE  2006       4          11         CWQR2006004      120060308G341168C48           DRAIN VALVE                             CESSNA560   560XL       2076702CE                                                               STATIC SYSTEM   LOOSE           B  DXTAK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05648QS                       5605574                                 FOUND THE STATIC SYSTEM DRAIN VALVE POPPET RETAING RING COMING LOOSE FROM VALVE BASE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F    RTA22CE                        
20060324000342006032400034CE  2006       3          24         CWQR2006005      120060308G341168C48           DRAIN VALVE                             CESSNA560   560XL       2076702CE                                                               STATIC SYS      LOOSE           B  DXTAK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05609QS                       5605522                                 FOUND THE STATIC SYSTEM DRAIN VALVE POPPET RETAINING RING COMING LOOSE FROM VALVE BASE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F    RTA22CE                        
20060411000492006041100049CE  2006       4          11         CWQR2006006      120060308G341168C48           DRAIN VALVE                             CESSNA560   560XL       2076702CE                                                                               LOOSE           B  DXTAK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05650QS                       5605150                                 FOUND THE STATIC SYSTEM DRAIN VALVE POPPET RETAING RING COMING LOOSE FROM VALVE BASE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F    RTA22CE                        
20060411000502006041100050CE  2006       4          11         CWQR2006007      120060308G341168C48           DRAIN VALVE                             CESSNA560   560XL       2076702CE                                                                               LOOSE           B  DXTAK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05664QS                       5605264                                 FOUND THE STATIC SYSTEM DRAIN VALVE POPPET RETAING RING COMING LOOSE FROM VALVE BASE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F    RTA22CE                        
20060331001162006033100116CE  2006       3          31         CWQR2006008      120060308G3411                RETAINER                                CESSNA560   560XL       2076702CE                                                               DRAIN VALVE     LOOSE           B  DXTAK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05651QS                       5605251                                 FOUND THE STATIC SYSTEM DRAIN VALVE POPPET RETAINING RING COMING LOOSE FROM VALVE BASE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F    RTA22CE                        
20060501002462006050100246CE  2006       5          1          CWQR2006009      120060417G2701666000269       CABLE ASSY                              CESSNA560   560XL       2076702CE                                                               FUSELAGE        DAMAGED         B  DXTAK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05                                                                    DURING A SCHEDULED MAINTENANCE VISIT BEFORE REPLACING A CABLE ASSEMBLY ON A THE CABLE TERMINAL END WAS FOUND TO HAVE BEEN DRILLED TO A DEPTH OF .3750-.5 INCH AT AN ANGLE AND DAMAGED THE THREADS. THIS CABLE ASSEMBLY WAS ORDERED FROM AND DOCUMENTED AS NEW.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F    RTA22CE                        
20060501002472006050100247CE  2006       5          1          CWQR2006010      120060427G325055423043        FORK                                    CESSNA560   560XL       2076702CE                                                               NOSE STEERING   GOUGED          B  DXTAK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05638QS2260                   5605363                                 DURING AN INSPECTION FOUND THE NOSE GEAR STEERING LOWER FORK ASSY (5542304-3) GOUGED. FURTHER INVESTIGATION FOUND THE FORK ASSY IS GOUGED ONLY DURING A MAINTENANCE GEAR RETRACTION TEST, WHEN THE RUDDER PEDALS ARE DEFLECTED FULL RT AND LT. REMOVED FORK ASSY, MEASURED GOUGE WAS BEYOND LIMITS.  REPLACED FORK AND PREFORMED GEAR RETRACTION TEST, THE NEW FORK ASSY WAS MEASURED AND PREFORMED NDT, WAS WITHIN LIMITS IAW MM.  SUBMITTED SERVICE CONDITION REPORT MFG UNDER NR 234220 DATED 04/27/2006.                                                                                                                                                                                                                                    2L72 4F    RTA22CE                        
20060629001092006062900109CE  2006       6          29         CWQR2006011      120060626G2731666000134       CONTROL CABLE                           CESSNA560   560XL       2076702CE                                                               ELEVATOR TRIM   FRAYED          B  DXTAK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05692QS                       5605092                                 DURING A PHASE 1-4 INSPECTION THE ELEVATOR TRIM CABLE ASSEMBLY WAS FOUND TO BE FRAYED WHERE IT PASSES THROUGH THE HORIZONTAL STABILIZER.  THE CABLE APPEARS TO HAVE BEEN INSTALLED PROPERLY AND IT DOES NOT LOOK AS IF IT WAS DAMAGED DURING INSTALLATION.  AN SCR HAS BEEN SUBMITTED TO CESSNA CITATION UNDER 242171.                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA22CE                        
20060629001102006062900110CE  2006       6          29         CWQR2006012      120060626G2731666000134       CONTROL CABLE                           CESSNA560   560XL       2076702CE                                                               ELEVATOR TRIM   FRAYED          B  DXTAK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05684QS                       5605084                                 DURING A PHASE 1-4 INSPECTION THE ELEVATOR TRIM CABLE ASSEMBLY WAS FOUND TO BE FRAYED WHERE IT PASSES THROUGH THE HORIZONTAL STABLIZER. THE CABLE APPEARS TO HAVE BEEN INSTALLED PROPERLY AND IT DOES NOT LOOK AS IF IT WAS DAMAGED DURING INSTALLATION.  AN SCR HAS BEEN SUBMITTED TO CESSNA CITATION UNDER 242172.                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F    RTA22CE                        
20060714000582006071400058CE  2006       7          14         CWQR2006013      120060628G2731666000134       CONTROL CABLE                           CESSNA560   560XL       2076702CE                                                               ELEVATOR        FRAYED          B  DXTAK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05671QS                       5605071                                 DURING A PHASE 1-4 INSPECTION THE ELEVATOR TRIM CABLE ASSEMBLY WAS FOUND TO BE FRAYED WHERE IT PASSES THROUGH THE HORIZONTAL STABILIZER. THE CABLE APPEARS TO HAVE BEEN INSTALLED PROPERLY AND DOES NOT LOOK AS IF IT WAS DAMAGED DURING INSTALLATION. AN SCR HAS BEEN SUBMITTED TO CESSNA CITATION UNDER # 242686                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F    RTA22CE                        
20060719000012006071900001CE  2006       7          19         CWQR2006014      120060712G2731666000134       CABLE ASSY                              CESSNA560   560XL       2076702CE                                                               ELEVATOR TRIM   FRAYED          B  DXTAK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05637QS                       5605137                                 REQUESTED CABLE INSPECTION OF AFT ELEVATOR TRIM CABLE, BECAUSE AC IN THE FLEET OF THIS SN BLOCK AND TIME SHOWED SIGNS OF FRAYING. DURING INSPECTION FOUND THE CABLE FRAYED AS IT TRANSVERSED THE PULLEY. REMOVED CABLE AND CHAIN ASSEMBLY AND PREFORMED LOOP CHECK, THIS SHOWED MORE STRANDS BROKEN THEN WHEN VISUALLY INSPECTED ON AIRCRAFT.  PRIOR TO REMOVAL THE CABLE TENSION WAS CHECKED AND FOUND TO BE WITHIN LIMITS, CABLE AND PULLEYS HAD GOOD ALIGNMENT AND NO ABNORMAL WEAR ON THE PULLEYS. AN SCR HAS BEEN SUBMITTED TO MFG UNDER NR 244358                                                                                                                                                                                         2L72 4F    RTA22CE                        
20060725002372006072500237CE  2006       7          25         CWQR2006015      120060717G2731666000134       CABLE                                   CESSNA560   560XL       2076702CE                                                               ELEVATOR TRIM   FRAYED          B  DXTAK   NONE                                                                                            P  NO WARNING INDICATION                                                         ININSP/MAINT     1                      GL05690QS                       5605090                                 DURING A SCHEDULED INSP ON THIS AIRCRAFT THE OPERATOR REQUESTED THAT WE INSPECT THE AFT CABLES ON THE ELEVATOR TRIM SYSTEM. PRIOR TO REMOVAL WE CHECKED THE CABLE TENSION, FOUND IT TO BE 30 LBS CABLE TENSION SHOULD BE 45 +/-5 LBS AT 75 DEGREES.  INSP AFTER THE CABLE WAS REMOVED REVEALED 1 COMPLETE STRAND BROKE AND SEVERAL WIRES. THE DAMAGED AREA WAS LOCATED DIRECTLY OVER THE PULLEY WHEN THE TAB IS IN THE 2-3 DEGREE DOWN POSITION. THIS IS THE FIFTH ELEVATOR TRIM CABLE THIS REPAIR STATION HAS FOUND DAMAGED ON THIS MODEL AIRCRAFT WITH TOTAL TIME OF 5000 +/-500 HOURS. AN SCR HAS BEEN SUBMITTED TO MFR UNDER NR 244926                                                                                                      2L72 4F    RTA22CE                        
20060816003092006081600309CE  2006       8          16         CWQR2006016      120060728G2731666015021       CONTROL CABLE                           CESSNA560   560XL       2076702CE                                                               ELEVATORS       FRAYED          B  DXTAK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05694QS                       5605194                                 DURING PHASE 1-4 INSPECTION, IAW OPERATOR REQUEST WE INSPECTED THE AFT ELEVATOR TRIM CABLES. UPON INSPECTION WE FOUND A SINGLE BROKEN WIRE. REMOVED CABLE AND PREFORMED LOOP TEST AND FOUND SEVERAL MORE BROKEN WIRES. PRIOR TO DISASSEMBLY THE CABLE TENSION, WAS WITHIN MM LIMITS. INSPECTED CABLE ROUTING AND PULLEYS, ALL CHECKED GOOD. AN SCR HAS BEEN SUBMITTED UNDER NR 246824.                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA22CE                        
20060814001442006081400144CE  2006       8          14         CWQR200617       120060731G2731666015011       CONTROL CABLE                           CESSNA560   560XL       2076702CE                                                               ELEVATOR TRIM   FRAYED          B  DXTAK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05687QS                       5605187                                 DURING PHASE B INSPECTION, IAW OPERATOR REQUEST, INSPECTED THE AFT ELEVATOR TRIM CABLES. UPON INSPECTION WE FOUND 3 BROKEN WIRES. REMOVED CABLE AND PREFORMED LOOP TEST AND FOUND SEVERAL BROKEN WIRES IN EACH STRAND. THE BROKEN WIRES WERE FOUND IN THE AREA AS IT CROSSES THE PULLEY, WITH TAB NEUTRAL TO 1-2 DEGREES DOWN. PRIOR TO DISASSEMBLY THE CABLE TENSION WAS CHECKED, WAS WITHIN MM LIMITS. INSPECTED CABLE ROUTING AND PULLEYS, ALL CHECKED GOOD. AN SDR HAS BEEN SUBMITTED TO MFG UNDER NR 246824.                                                                                                                                                                                                                               2L72 4F    RTA22CE                        
20060825000412006082500041CE  2006       8          25         CWQR200618       120060807G2731666000133       CABLE ASSY                              CESSNA560   560XL       2076702CE                                                               ELEVATOR TRIM   FRAYED          B  DXTAK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05659QS                       5605359                                 DURING A PHASE B INSPECTION, OPERATOR REQUESTED WE INSPECT THE AFT ELEVATOR TRIM CABLES. UPON INSPECTION WE FOUND BROKEN WIRES, TOOK CABLE TENSIONS, FOUND TO BE WITHIN LIMITS AND CABLE WAS CENTERED IN PULLEY. THE CABLE WAS REMOVED AND LOOP TEST SHOWED MORE BROKEN WIRES. THE WEAR ON THE CABLE APPEARS TO BE IN THE SAME LOCATION THAT WE FOUND ON THE PREVIOUS SIRS SUBMITTED. THAT BEING 0 TO 2 DEGREES TAB DOWN AND FRAYED AREA CENTERED ON PULLEY. AN SCAR HAS BEEN SUBMITTED TO MFG UNDER NR 248175.                                                                                                                                                                                                                                 2L72 4F    RTA22CE                        
20060825000512006082500051CE  2006       8          25         CWQR200619       120060809G2731666000133       CABLE ASSY                              CESSNA560   560XL       2076702CE                                                               ELEVATOR TRIM   FRAYED          B  DXTAK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05605QS                       5605321                                 DURING A PHASE B INSPECTION, OPERATOR REQUESTED WE INSPECT THE AFT ELEVATOR TRIM CABLES. UPON INSPECTION WE FOUND BROKEN WIRES, TOOK CABLE TENSIONS, FOUND TO BE WITHIN LIMITS AND CABLE WAS CENTERED IN PULLEY.  THE CABLE WAS REMOVED AND LOOP TEST SHOWED MORE BROKEN WIRES.  THE WEAR ON THE CABLE APPEARS TO BE IN THE SAME LOCATION THAT WE FOUND ON THE PREVIOUS SDRS SUBMITTED. THAT BEING 0 TO 2 DEGREES TAB DOWN AND FRAYED AREA CENTERED ON PULLEY. AN SCR HAS BEEN SUBMITTED TO UNDER NR 248556.                                                                                                                                                                                                                                    2L72 4F    RTA22CE                        
20060825000342006082500034CE  2006       8          25         CWQR200620       120060814G2731666000133       CONTROL CABLE                           CESSNA560   560XL       2076702CE                                                               ELEVATOR TRIM   FRAYED          B  DXTAK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05610QS                       5605210                                 DURING A PHASE B-INSPECTION, OPERATOR REQUESTED WE INSPECT THE AFT ELEVATOR TRIM CABLES. UPON INSPECTION WE FOUND BROKEN WIRES, TOOK CABLE TENSIONS, FOUND TO BE WITHIN LIMITS AND CABLE WAS CENTERED IN PULLEY.THE CABLE WAS REMOVED AND LOOP TEST SHOWED MORE BROKEN WIRES.  THE WEAR ON THE CABLE APPEARS TO BE IN THE SAME LOCATION THAT WE FOUND ON THE PREVIOUS SDRS SUBMITTED. THAT BEING 0 TO 2 DEGREES TAB DOWN AND FRAYED AREA CENTERED ON PULLEY. AN SCR HAS BEEN SUBMITTED TO UNDER NR 249122.                                                                                                                                                                                                                                      2L72 4F    RTA22CE                        
20060825000352006082500035CE  2006       8          25         CWQR200621       120060821G2731666000133       CONTROL CABLE                           CESSNA560   560XL       2076702CE                                                               ELEVATOR TRIM   FRAYED          B  DXTAK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05640QS                       5605240                                 DURING A PHASE B-INSPECTION, OPERATOR REQUESTED WE INSPECT THE AFT ELEVATOR TRIM CABLES. UPON INSPECTION WE FOUND BROKEN WIRES, TOOK CABLE TENSIONS, FOUND TO BE WITHIN LIMITS AND CABLE WAS CENTERED IN PULLEY. THE CABLE WAS REMOVED AND LOOP TEST SHOWED MORE BROKEN WIRES. THE WEAR ON THE CABLE APPEARS TO BE IN THE SAME LOCATION THAT WE FOUND ON THE PREVIOUS SDRS SUBMITTED. THAT BEING 0 TO 2 DEGREES TAB DOWN AND FRAYED AREA CENTERED ON PULLEY. AN SCR HAS BEEN SUBMITTED TO MFG UNDER NR 250170.                                                                                                                                                                                                                                  2L72 4F    RTA22CE                        
20060825000162006082500016CE  2006       8          25         CWQR200622       120060821G2731666000134       CONTROL CABLE                           CESSNA560   560XL       2076702CE                                                               ELEVATOR TRIM   FRAYED          B  DXTAK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05621QS                       5605280                                 DURING A PHASE B-INSPECTION, OPERATOR REQUESTED, INSPECT THE AFT ELEVATOR TRIM CABLES. UPON INSPECTION FOUND BROKEN WIRES, TOOK CABLE TENSIONS, FOUND TO BE WITHIN LIMITS AND CABLE WAS CENTERED IN PULLEY. THE CABLE WAS REMOVED AND LOOP TEST SHOWED MORE BROKEN WIRES. THE WEAR ON THE CABLE APPEARS TO BE IN THE SAME LOCATION THAT WE FOUND ON THE PREVIOUS SDRS SUBMITTED. THAT BEING 0 TO 2 DEGREES TAB DOWN AND FRAYED AREA CENTERED ON PULLEY. AN SCR HAS BEEN SUBMITTED TO MFG UNDER NR 250168.                                                                                                                                                                                                                                       2L72 4F    RTA22CE                        
20060825000322006082500032CE  2006       8          25         CWQR200623       120060821G2720666000228       CONTROL CABLE                           CESSNA560   560XL       2076702CE                                                               RUDDER          FRAYED          B  DXTAK   NONE                                                                                            P  NO WARNING INDICATION                                                         ININSP/MAINT     1                      GL05                                                                    THE CABLE ASSEMBLY WAS RECEIVED FROM MFG, WITH AN 8130 SHOWING IT TO BE NEW. THE CABLE HAS SEVERAL BROKEN WIRES THAT APPEARS TO BE A MANUFACTURING DEFECT. THIS REPORT AND PICTURES WILL BE FORWARDED TO THE OPERATOR AND MFG. AN SCR HAS BEEN SUBMITTED TO MFG UNDER NR 250181.                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F    RTA22CE                        
20060913001452006091300145CE  2006       9          13         CWQR200624       120060821G2740666000134       CONTROL CABLE                           CESSNA560   560XL       2076702CE                                                               ELEVATOR TRIM   BROKEN          B  DXTAK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05668QS                       5605268                                 DURING A PHASE 1-4 INSPECTION, OPERATOR REQUESTED WE INSPECT THE AFT ELEVATOR TRIM CABLES. UPON INSPECTION WE FOUND BROKEN WIRES. TOOK CABLE TENSIONS, FOUND TO BE WITHIN LIMITS AND CABLE WAS CENTERED ON THE PULLEYS. THE CABLE WAS REMOVED AND LOOP TEST SHOWED MORE BROKEN WIRES. AN SCR HAS BEEN SUBMITTED TO MFG UNDER NR 250293.                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F    RTA22CE                        
20060922001052006092200105CE  2006       9          22         CWQR200625       120060829G2720666000134       CONTROL CABLE                           CESSNA560   560XL       2076702CE                                                               TRIM            BROKEN          B  DXTAK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05646QS                       5605246                                 DURING A ROUTINE MAINTENANCE VISIT, OPERATOR REQUESTED WE INSPECT THE AFT ELEVATOR TRIM CABLES. UPON INSPECTION WE FOUND ABOUT .333 OF THE CABLE STRANDS BROKEN. TOOK CABLE TENSIONS, FOUND TO BE WITHIN LIMITS AND CABLE WAS CENTERED ON THE PULLEYS. THE CABLE APPEARS TO HAVE THE MOST DAMAGE CENTERED ON THE PULLEY WITH THE ELEVATOR TRIM TAB IN THE NEUTRAL TO 1-2 DEGREE DOWN POSITION. AN SCR HAS BEEN SUBMITTED TO MFG UNDER NR 251700.                                                                                                                                                                                                                                                                                                2L72 4F    RTA22CE                        
20060518002322006051800232EU  2006       5          18         D20060502        120060502G5313                LONGERON                                LET   L23   L23         1360308EU                                                               REAR COCKPIT    CRACKED         B  PF5RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM03420BA                       029007                                  FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LH RUDDER PEDAL, DURING A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF ALL MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT WHILE ACTUATING THE RUDDER PEDAL - CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCREWS.                                                                                                                                                                                                                                            1K00       RCG24EU                        
20070108002752007010800275WP  2007       1          8          DJSA20061202     220061202G7200TFE7315BR2C     ENGINE                                  AMD   FALC20FALCON20C5  2730107EU  GARRTTTFE731TFE7315BR        WP                                              FAILED          E  DJSRA   UNSCHED LANDING                                                                                 YJ ENGINE STOPPAGE           WARNING INDICATION                                  CLCLIMB          1                      GL23531FL5815 961               113         P95155C                     UNCONTAINED ENGINE FAILURE DURING CLIMB AT 600 FEET AGL.  AIRCRAFT RETURNED, MAKING AN UNEVENTFUL LANDING.  ENGINE HAS BEEN RETURNED TO MANUFACTURER FOR TEARDOWN AND EVALUATION TO DETERMINE CAUSE OF FAILURE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA7EU    E6WE                 
20060518002292006051800229EU  2006       5          18         DOSS002          120060502G5313                LONGERON                                LET   L23   L23         1360308EU                                                               REAR COCKPIT    CRACKED         B  PF5RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM03420BA                       029007                                  FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LH RUDDER PEDAL, DURING A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF ALL MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT WHILE ACTUATING THE RUDDER PEDAL - CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCREWS.                                                                                                                                                                                                                                            1K00       RCG24EU                        
20060518001972006051800197EU  2006       5          18         DOSS01           120060502G5313                LONGERON                                LET   L23   L23         1360308EU                                                               ZONE 200        CRACKED         B  PF5RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM03434BA1330                   029011                                  LONGERON WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LT RUDDER PEDAL, DURING A SCHEDULED INSPECTION. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT WHILE ACTUATING THE RUDDER PEDAL, CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCREWS.  THIS WAS ENCOUNTERED ON TWELVE OUT OF SEVENTEEN AIRCRAFT (L13AC AND L23).                                                                                                                                                                                                                                                                                        1K00       RCG24EU                        
20060518002282006051800228EU  2006       5          18         DOSS02           120060502G5313                LONGERON                                LET   L23   L23         1360308EU                                                               REAR COCKPIT    CRACKED         B  PF5RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM03420BA                       029007                                  FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LT RUDDER PEDAL, DURING A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF ALL MDS.  IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT WHILE ACTUATING THE RUDDER PEDAL, CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCREWS.                                                                                                                                                                                                                                            1K00       RCG24EU                        
20060522002112006052200211EU  2006       5          22         DOSS03           120060502G5313                LONGERON                                LET   L23   L23         1360308EU                                                               REAR COCKPIT    CRACKED         B  PF5RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM03426BA1115 92                029008                                  FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LH RUDDER PEDAL, DURING A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF ALL MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT WHILE ACTUATING THE RUDDER PEDAL, CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCREWS.                                                                                                                                                                                                                                             1K00       RCG24EU                        
20060518002332006051800233EU  2006       5          18         DOSS04           120060502G5313                LONGERON                                LET   L23   L23         1360308EU                                                               REAR COCKPIT    CRACKED         B  PF5RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM03427BA873  14                029009                                  FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LT RUDDER PEDAL, DURING A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF ALL MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT WHILE ACTUATING THE RUDDER PEDAL - CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCREWS.                                                                                                                                                                                                                                            1K00       RCG24EU                        
20060530001682006053000168EU  2006       5          30         DOSS05           120060502G5313                LONGERON                                LET   L23   L23         1360308EU                                                               REAR COCKPIT    CRACKED         B  PF5RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM03428BA1123 5                 029010                                  FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE REAR COCKPIT (RCP) LT RUDDER PEDAL DURING A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF ALL MODELS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT WHILE ACTUATING THE RUDDER PEDAL - CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCREWS.                                                                                                                                                                                                                           1K00       RCG24EU                        
20060518002342006051800234EU  2006       5          18         DOSS06           120060502G5313                LONGERON                                LET   L23   L23         1360308EU                                                               REAR COCKPIT    CRACKED         B  PF5RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM03430BA1461                   029012                                  FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LT RUDDER PEDAL, DURING A SCHEDULED INSPECTION.   SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF ALL MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT WHILE ACTUATING THE RUDDER PEDAL - CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCREWS.                                                                                                                                                                                                                                          1K00       RCG24EU                        
20060518002352006051800235EU  2006       5          18         DOSS07           120060502G5313                LONGERON                                LET   L23   L23         1360308EU                                                               REAR COCKPIT    CRACKED         B  PF5RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM03431BA1120 68                029013                                  FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LT RUDDER PEDAL, DURING A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF ALL MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT WHILE ACTUATING THE RUDDER PEDAL - CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCREWS.                                                                                                                                                                                                                                            1K00       RCG24EU                        
20060518002362006051800236EU  2006       5          18         DOSS08           120060502G5313                LONGERON                                LET   L23   L23         1360308EU                                                               REAR COCKPIT    CRACKED         B  PF5RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM03433BA978                    029014                                  FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LH RUDDER PEDAL, DURING A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF ALL MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT WHILE ACTUATING THE RUDDER PEDAL - CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCREWS.                                                                                                                                                                                                                                            1K00       RCG24EU                        
20060518002372006051800237EU  2006       5          18         DOSS10           120060502G5313                LONGERON                                LET   L23   L23         1360308EU                                                               REAR COCKPIT    CRACKED         B  PF5RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM03438BA524  41                029016                                  FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LT RUDDER PEDAL, DURING A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF ALL MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT WHILE ACTUATING THE RUDDER PEDAL - CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCREWS.                                                                                                                                                                                                                                            1K00       RCG24EU                        
20060518002312006051800231EU  2006       5          18         DOSS102          120060502G5313                LONGERON                                LET   L23   L23         1360308EU                                                               REAR COCKPIT    CRACKED         B  PF5RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM03420BA                       029007                                  FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LT RUDDER PEDAL, DURING A SCHEDULED INSPECTION.  SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF ALL MDS.  IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT WHILE ACTUATING THE RUDDER PEDAL - CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCREWS.                                                                                                                                                                                                                                          1K00       RCG24EU                        
20060518002382006051800238EU  2006       5          18         DOSS11           120060502G5313                LONGERON                                LET   L23   L23         1360308EU                                                               REAR COCKPIT    CRACKED         B  PF5RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM03419BA1320 71                029006                                  FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LT RUDDER PEDAL, DURING A SCHEDULED INSPECTION.  SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF ALL MDS.  IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT WHILE ACTUATING THE RUDDER PEDAL - CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCREWS.                                                                                                                                                                                                                                          1K00       RCG24EU                        
20060530001632006053000163EU  2006       5          30         DOSS12           120060502G5313                LONGERON                                LET   L13   L13ACBLANIK 1360312EU                                                               REAR COCKPIT    CRACKED         B  PF5RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM03422BA1109 54                028903                                  FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE REAR COCKPIT (RCP) LT RUDDER PEDAL, DURING A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF ALL MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT, MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT WHILE ACTUATING THE RUDDER PEDAL - CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCREWS.                                                                                                                                                                                                                                   1K00         G24EU                        
20060518002582006051800258EU  2006       5          18         DOSS13           120060502G5313                LONGERON                                LET   L23   L23         1360308EU                                                               REAR COCKPIT    CRACKED         B  PF5RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM03410BA1109 54                029005                                  FIRST LONGERON (N434BA) WAS FOUND CRACKED AT THE ELEVATOR TRIM GUIDE ATTACH POINT, NEAR THE RCP LT RUDDER PEDAL, DURING A SCHEDULED INSPECTION. SUBSEQUENT FINDINGS OCCURRED AS RESULT OF QUALITY DEPARTMENT ISSUING A ONE TIME INSPECTION OF ALL MDS. IT LOOKS AS IF THE OPERATOR, IN THE REAR COCKPIT (RCP), MAY BE STRIKING THE ELEVATOR TRIM GUIDE WITH HIS/HER FOOT WHILE ACTUATING THE RUDDER PEDAL, CAUSING THE SUPPORT STRUCTURE (LONGERON) TO WEAKEN AND FORM CRACKS AT THE ATTACH SCREWS.                                                                                                                                                                                                                                             1K00       RCG24EU                        
20061013000402006101300040WP  2006       10         13         DSC4L6255        220061003G721018118           BEARING                                                                    GARRTTTPE331TPE33111U   01514WP                              GEARBOX         FAILED          B  DSC4K   NONE                                                                                            J  WARNING INDICATION                                                            ININSP/MAINT     1                      SO15     6475                               P44628C                     ENGINE RECEIVED FOR REPORTED METAL IN OIL.  UPON DISASSEMBLY, FOUND BEARING PN: 18118 (FAA-PMA REPLACEMENT  PN: 3103585-1) INSTALLED IN ACCESSORY GEAR ASSY PN: 3103598-1 HAD FAILED, CAUSING MULTIPLE ACCESSORY GEAR DAMAGE AND METAL CONTAMINATION IN GEARBOX / OIL SYSTEM.                                                                                                                                                                                                                                                                                                                                                                                                                                                                          4  T          E4WE                 
20060411000272006041100027NM  2006       4          11         DU4R2006342      120060313G5330                SKIN                                    BOEING727   727223      1384074NM                                                               BS 1074 S18-19L DENTED          B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15289MT                       22467                                   FUSELAGE SKIN DENTED AT BS 1074 BETWEEN S-18L - 19L.     CUT OUT DENTED AREA IAW B727 SRM 53-30-2 FIG. 1 HFEC AROUND CUT OUT PER D6-48875, PT 6, 51-10-00 FIG. 23. NO RELEVANT INDICATION NOTED. FABRICATED AND INSTALLED REPAIR DOUBLER 12" X 11.7" X 7.55" FROM 2024-T3 .063 IAW B727 SRM 51-30-3 FIG. 1, 51-10-2, 51-30-2, 53-30-3 CLASS "A" REPAIR.                                                                                                                                                                                                                                                                                                                                                                                         2L73 4F      A3WE                         
20060411000282006041100028NM  2006       4          11         DU4R2006343      120060313G5330                SKIN                                    BOEING727   727223      1384074NM                                                               BS 1079         DENTED          B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15289MT                       22467                                   FUSELAGE SKIN DENTED AT BS 1079 BETWEEN S-13-14L.   CUT OUT DENTED AREA IAW B727 SRM 53-30-3 FIG. 13A. FABRICATED AND INSTALLED REPAIR DOUBLER 5.80 DIAMETER FROM 2024-T3 .090 IAW B727 SRM  51-10-2 PG. 7, AMM 51-20-23 PG. 704. CLASS "A" REPAIR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L73 4F      A3WE                         
20060411000242006041100024NM  2006       4          11         DU4R2006344      120060320G5330                SKIN                                    BOEING727   727223      1384074NM                                                               BS 1145         DENTED          B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15289MT                       22467                                   FUSELAGE SKIN DENTED AT BS 1145 BETWEEN S18-19L.   FABRICATED AND INSTALLED REPAIR DOUBLER 10-3/4" X 9" FROM 2024-T3 .063 IAW B727 SRM  53-30-3 AND 51-30-2. CLASS "A" REPAIR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L73 4F      A3WE                         
20060411000262006041100026NM  2006       4          11         DU4R2006345      120060322G531565255896        FLOORBEAM                               BOEING727   727223      1384074NM                                                               BS 760 RBL 1    CRACKED         B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15289MT                       22467                                   CRACK IN CABIN FLOOR SUPPORT BS 760 RBL 1.    REMOVED AND REPLACED FLOOR SUPPORT WITH  IAW B727 SRM  51-30-2 AND 51-30-5.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L73 4F      A3WE                         
20060411000232006041100023NM  2006       4          11         DU4R2006346      120060326G5310                STRUCTURE                               BOEING727   727223      1384074NM                                                               BS 1166         CORRODED        B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15289MT                       22467                                   RT AFT LAV SUB FLOOR HAS CORROSION IN SEVERAL PLACES AT BS 1166. CUT OUT CORROSION. FABRICATED AND INSTALLED WEB REPAIR 15-3/4" X 4-3/4" FROM 2024-T3 .071 IAW B727 SRM  51-40-2, 51-30-2, 51-10-2 AND AMM 51-20-23.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L73 4F      A3WE                         
20060411000252006041100025NM  2006       4          11         DU4R2006347      120060326G5347656426110       SEAT TRACK                              BOEING727   727223      1384074NM                                                               BS1120-1133     CORRODED        B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15289MT                       22467                                   CORROSION ON LT O/B SEAT TRACK BS 1100-1133.  REMOVED CORRODED SEAT TRACK FROM BS 1070 TO BS 1137 AND REPLACED IAW B727 SRM 51-30-2, 51-10-2 AND AMM 51-20-23.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L73 4F      A3WE                         
20060411000222006041100022NM  2006       4          11         DU4R2006355      120060331G5330                SKIN                                    BOEING727   727223      1384074NM                                                               BS 1137 S20L    DENTED          B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15289MT                       22467                                   FUSELAGE SKIN BELOW NR 1 ENGINE DENTED AT LAP SEAM BS 1137 S-20L.  CUT OUT DENTED AREA. FABRICATED AND INSTALLED EXTERNAL REPAIR 7.75" X 9.25" X5.75" X 2.5" FROM 20240-T3 .063 AND LAP SPLICE REPAIR 10" X 4.25" X 4.5" X 2.75" X 4.5" FROM 2024-T3 .050 IAW B727 SRM 53-30-3 FIG. 5, 51-10-3.                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L73 4F      A3WE                         
20060518001782006051800178NM  2006       5          18         DU4R2006358      120060412G5752                TAB                                     BOEING727   727223      1384074NM                                                               RT AILERON      DELAMINATED     B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15289MT                       22467                                   S/O 304001; NR 21453 - RT IB AILERON TAB DELAMINATED AT LOWER SURFACE OUTER L/E AREA.  CUT OUT DISBONDED SKIN. FABRICATED AND BONDED DOUBLER 10.5  X 3.7500 INCH X 9 X 3.5 X 2.2500 INCH AND FILLER 8 INCH X 1.7500 INCH X 7.2500 INCH X 1 INCH X 1 INCH FROM 2024-T3, .012 IAW SRM 51-40-20 PG. 14, 15, 42 - 47 AND 62, 51-60-3 AND 51-80-3.                                                                                                                                                                                                                                                                                                                                                                                                   2L73 4F      A3WE                         
20060512001592006051200159NM  2006       5          12         DU4R2006359      120060412G5753                FLAP                                    BOEING727   727223      1384074NM                                                               LT WING         DELAMINATED     B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15289MT                       22467                                   S/O 304001   N/R 21634 - LT IB FORE FLAP UPPER SIDE HAS DISBOND AFT OF CENTER ACCESS PANEL.  CUT OUT DISBONDED UPPER SKIN AND HONEYCOMB. FABRICATED AND BONDED DOUBLERS 13-5/8" X 11" AND 12-1/2" X 11-1/4"  AND 9-1/4" X 8? X 5" X 5" X 5" FROM 2024-T3 .016 AND AND 2 EA. HONEYCOMB REPAIRS 9-1/4" X 5" X 5" X 5" X 8" FROM BMS4-4 IAW B727 SRM 57-50-2 PG. 5, 51-40-20 PG. 15, 22, 23, 44 - 47, 53-57, 59, 62 AND 51-40-23 PG. 1-8.                                                                                                                                                                                                                                                                                                          2L73 4F      A3WE                         
20060518002602006051800260NM  2006       5          18         DU4R200636       120060412G5320                FLOOR SUPPORT                           BOEING727   727223      1384074NM                                                               FUSELAGE        CORRODED        B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15289MT                       22467                                   S/O 304001)  N/R 21660, CORROSION ON FLOOR SUPPORT THAT ATTACHES TO CUSP WEB AT BS 1070 - 1030 LT.  MECHANICALLY REMOVED CORROSION FOUND OUT OF LIMITS.  CUT AND TRIMMED CORRODED SECTION. FABRICATED AND INSTALLED FLOOR SUPPORT ANGLES 88.0 INCHES X 4.50 FROM 7075-T6 .080 AND 10.0INCHES X 1.80 INCHES X 1.50 INCHES 7075-T6 .090 IAW SRM 51-30-2.                                                                                                                                                                                                                                                                                                                                                                                          2L73 4F      A3WE                         
20060518002262006051800226NM  2006       5          18         DU4R2006360      120060412G5753                FLAP                                    BOEING727   727223      1384074NM                                                               LT WING         CHAFED          B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15289MT                       22467                                   S/O 304001)  N/R 21637 - LT IB FORE FLAP UNDER SIDE LEADING EDGE 8 INCHES FROM OB END HAS CHAFED AREA.  BLENDED CHAFED AREA, FOUND OUT OF LIMITS, FABRICATED AND INSTALLED DOUBLER 3.750 INCHES X 6.0 INCHES FROM 2024-T3 .063 IAW SRM 57-50-04 PG. 2-3.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L73 4F      A3WE                         
20060518002272006051800227NM  2006       5          18         DU4R2006361      120060412G5753                FLAP                                    BOEING727   727223      1384074NM                                                               LT WING         DEBONDED        B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15289MT                       22467                                   S/O 304001)   N/R 21640 - LT IB FT FLAP IB END HAS AREA OF DEBOND.  REPAIRED BY CLEANING, PREPPED AND REPAIRED IAW SRM 51-40-21 FIG. 1.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L73 4F      A3WE                         
20060518002252006051800225NM  2006       5          18         DU4R2006362      120060412G5347BAC1518338      FLOORBEAM                               BOEING727   727223      1384074NM                                                               FUSELAGE        CORRODED        B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15289MT                       22467                                   S/O 304001)  N/R 21652 - CORROSION ON BS 1070 LBL 10 FLOOR BEAM.  CUT OUT CORRODED AREA.  FABRICATED AND INSTALLED FLOORBEAM REPAIR 22.20 INCHES FROM BAC1505-100617 7075-T73 AND 22.20 INCHES FROM BAC1490-2831 7075-T6 IAW SRM 53-10-8 FIG. 8, AND 51-10-1.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L73 4F      A3WE                         
20060518002242006051800224NM  2006       5          18         DU4R2006363      120060412G5347BAC1518338      SEAT TRACK                              BOEING727   727223      1384074NM                                                               FUSELAGE        CORRODED        B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15289MT                       22467                                   S/O 304001, N/R 21653 - CORROSION ON IB SIDE OF SEAT TRACK ALONG RADIUS AT BS 1090 - 1030 LBL 40.   CUT OUT CORRODED AREA OF SEAT TRACK.  FABRICATED AND INSTALLED SEAT TRACK REPAIR 18 INCHES X 3.5 FROM BAC1520-792 IAW SRM 51-30-2, 51-20-2 AND 51-10-1.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L73 4F      A3WE                         
20060518002492006051800249NM  2006       5          18         DU4R2006364      120060412G5347656426110       SEAT TRACK                              BOEING727   727223      1384074NM                                                               FUSELAGE        CORRODED        B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15289MT                       22467                                   S/O 304001)  N/R 21656, CORROSION ON LT OB SEAT TRACK AT BS 1080.  MECHANICALLY REMOVED CORROSION FOUND OUT OF LIMITS.  REMOVED AND REPAIRED SEAT TRACK WITH P/N 65-64261-10 IAW SRM 51-30-2.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L73 4F      A3WE                         
20060518002592006051800259NM  2006       5          18         DU4R2006365      120060412G5320                FLOOR SUPPORT                           BOEING727   727223      1384074NM                                                               FUSELAGE        CORRODED        B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15289MT                       22467                                   S/O 304001) N/R 21660, CORROSION ON FLOOR SUPPORT THAT ATTACHES TO CUSP WEB AT BS 1070 - 1030 LT.  MECHANICALLY REMOVED CORROSION FOUND OUT OF LIMITS.  CUT AND TRIMMED CORRODED SECTION. FABRICATED AND INSTALLED FLOOR SUPPORT ANGLES 88.0 INCH X 4.50 FROM 7075-T6 .080 AND 10.0 INCHES X 1.80 INCHES X 1.50 INCHES 7075-T6 .090 IAW SRM 51-30-2.                                                                                                                                                                                                                                                                                                                                                                                            2L73 4F      A3WE                         
20060518002502006051800250NM  2006       5          18         DU4R2006366      120060412G5330                SKIN                                    BOEING727   727223      1384074NM                                                               FUSELAGE        GOUGED          B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15289MT                       22467                                   S/O 304001)   N/R 21743,  2 GOUGES IN SKIN ON LT SIDE OF FS 460 AND 4 INCHES BELOW S-14 BELOW NR 5 WINDOW.  FABRICATED AND INSTALLED 2 EA. DOUBLERS 4.5 INCH AND 4.3 DIAMETER FROM 2024-T3 .071 AND 1 EA, .7500 INCH DIAMETER FROM 2024-T3 .050 IAW SRM 53-30-3 FIG. 13, MM 25-21-01.                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L73 4F      A3WE                         
20060518002702006051800270NM  2006       5          18         DU4R2006367      120060412G5754                SKIN                                    BOEING727   727223      1384074NM                                                               RT WING SLAT    DENTED          B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15289MT                       22467                                   S/O 304001, N/R 23584 - RT WING NR 5 SLAT TOPSIDE L/E DENTED.  CUT OUT DENT THAT WAS OUT OF LIMITS. FABRICATED AND INSTALLED REPAIR SKIN DOUBLER 5.5 INCH X 5.5 INCH FROM 2024-T3 .016 AND 2 EA.  SKIN REPAIR DOUBLERS 4.1 INCH X 4.1 INCH AND 1.6 INCH X 1.6 INCH 2024-T3 .040 IAW SRM 55-50-3 FIG. 1, AND 51-30-2.                                                                                                                                                                                                                                                                                                                                                                                                                            2L73 4F      A3WE                         
20060518002642006051800264NM  2006       5          18         DU4R2006368      120060412G5751                AILERON                                 BOEING727   727223      1384074NM                                                               RT WING         DENTED          B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15289MT                       22467                                   S/O 304001)  N/R 24581, RT WING IB AILERON NUMEROUS DENTS.   REMOVED DENTED SKIN. FABRICATED AND INSTALLED REPAIR SKIN DOUBLER 5.5 INCH X 5.5 INCH FROM 2024-T3 .016 AND 2 EA. SKIN REPAIR DOUBLER 24 INCH X 54 INCH FROM 2024-T3 .040 IAW SRM 51-10-2 AND 51-30-2.                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L73 4F      A3WE                         
20060518002512006051800251NM  2006       5          18         DU4R2006369      120060412G32306523369         FRAME                                   BOEING727   727223      1384074NM                                                               FUSELAGE        CORRODED        B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15289MT                       22467                                   S/O 304001)  N/R 24783  CORROSION FOUND INSIDE THE HOLE OF UPLOCK HOOK INSTALL FITTING BOTH FWD AND AFT SIDE.  REMOVED 2 EA BUSHINGS (REPAIR SLEEVES) IAW SOPM 32-32-51. REWORKED FRAME HOLE 9 IAW OHM 32-37-02 AND SRM 51-10-1. FABRICATED AND INSTALLED 2 EA. REPAIR SLEEVES IAW OHM 32-37-02 FIG. 404, 405 AND SOPM 20-50-3. REINSTALLED UPLOCK FRAME AND UPLOCK ASSY IAW MM 32-32-51.                                                                                                                                                                                                                                                                                                                                                       2L73 4F      A3WE                         
20060512000462006051200046NM  2006       5          12         DU4R2006370      120060414G5753                SKIN                                    BOEING727   727223      1384074NM                                                               RT WING,FOREFLAPDELAMINATED     B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15289MT                       22467                                   NR 24718  DENTED AND DISBONDED RT IB FORE FLAP UPPER SKIN 19 INCHES FROM IB EDGE.  REPAIRED DENTED AND DISBONDED RT IB FORE FLAP UPPER SKIN 19 INCHES FROM IB EDGE BY CUTTING OUT DELAMINATED AREA, APPROX 5 INCHES IN DIAMETER. FABRICATED AND INSTALLED DOUBLER AND FILLER 8 INCHES DIAMETER AND 5 INCHES FROM 2024-T3 .016 IAW SRM 51-40-20 PARA. 7, 8, 10, 14, 15, 18, 20, 21, 22.                                                                                                                                                                                                                                                                                                                                                          2L73 4F      A3WE                         
20060518001612006051800161NM  2006       5          18         DU4R2006371      120060414G5753                SKIN                                    BOEING727   727223      1384074NM  PWA   JT8   JT8D             NE                              LT FLAP         DELAMINATED     B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15289MT                       22467                                   N/R 24751)  FOUND SMALL AREA OF DELAMINATION OF UPPER IB SKIN LT IB FORE FLAP.  CUT OUT DELAMINATED (DISBONDED) AREA ON UPPER SKIN LT IB FORE FLAP. FABRICATED AND BONDED DOUBLER 6.5 X 5.6250 INCH AND FILLER 3.3750 INCH X 1.2500 INCH FROM 2024-T3 .016 IAW SRM 57-50-2 PG. 5, 51-40-20 PG. 11-16, 42-47, 57-59, AND 62.                                                                                                                                                                                                                                                                                                                                                                                                                     2L73 4F4  F  A3WE    E2EA                 
20060518001732006051800173NM  2006       5          18         DU4R2006372      120060414G5512                SKIN                                    BOEING727   727223      1384074NM  PWA   JT8   JT8D*            NE                              RT STABILIZER   TORN            B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15289MT                       22467                                   NR 24794  FOUND RT HORIZ STAB. T/E UPPER SKIN TORN BOTH IB AND OB SIDE OF NR3 BALANCE BAY STAB. STA. 157 AND 195 AFT OF AFT SPAR.  CUT OUT TORN SKIN OF RT HORIZ. STAB. T/E BOTH IB AND OB END OF NR3 BALANCE BAY.  FABRICATED AND INSTALLED DOUBLERS 10.8 X 5.3 INCHES, 4.7 X 4.6 INCHES AND 3.8 X .7 INCHES FROM 2024-T3 .032 IAW SRM 51-40-20 FIG. 1.                                                                                                                                                                                                                                                                                                                                                                                        2L73 4F4  F  A3WE    E2EA                 
20060510002512006051000251NE  2006       5          10         DU4R2006373      220060416G7230                DISC                                    BOEING727   727223      1384074NM  PWA   JT8   JT8D             NE                              ENGINE          UNSERVICEABLE   B  DU4RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO16289MT                       22467       702863                      S/O 304001 NR 24710 C-1 DISK REQUIRES REPLACEMENT.  PERFORMED VIBRATION CHECK ON NR 1 ENGINE AFTER C-1 DISK REPLACEMENT IAW P/W MM 72-00-00, PG. 571 TEST I AND MM 71-00-00 PG. 500. FOUND ALL VALVES WITHIN LIMITS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L73 4F4  F  A3WE    E2EA                 
20060926000632006092600063EA  2006       9          26         DYCR0596101      220060831G732225765362        FUEL CONTROL                            CESSNA172   172R        2072401CE  LYC   IO360 IO360L2A         EA                              ENGINE          MISOVERHAULED   B  DYCRO   OTHER                                                                                           Y  ENGINE STOPPAGE                                                               APAPPROACH       1                      GL07173QS4017 31                17280460    L2749851A                   A STUDENT PILOT WITH AN INSTRUCTOR ON BOARD WERE PRACTICING STALLS WHEN THE ENGINE CUT OFF, THEY WERE ABLE TO RESTART THE ENGINE WITHOUT FURTHER INCIDENT. DURING THE SAME FLIGHT, WHILE ON APPROACH FOR LANDING THE ENGINE CUT OFF AGAIN. THE STUDENT AND THE INSTRUCTOR WERE ABLE TO LAND THE AIRCRAFT ON THE RUNWAY WITHOUT INCIDENT. IN BOTH CASES THE PROPELLER WAS WINDMILLING. THE AIRCRAFT WAS TOWED TO MAINTENANCE FROM THE RUNWAY. MAINTENANCE CHECKED FUEL SYSTEM FOR FOD, LEAKS, CHECKED RIGGING AND COMPLIED WITH AD 2001-06-17. MAINTENANCE WAS UNABLE TO DUPLICATE PROBLEM ON THE GROUND. FUEL SERVO WAS STILL SUSPECT AFTER READING OTHER SDR'S ON LIKE MODEL AIRCRAFT WITH SIMILAR PROBLEMS SO SERVO WAS REMOVED AND SENT TO A 1H71 3O3  ONT3A12    1E10                 
20061031001662006103100166SO  2006       10         31         EDRCCUI          220061021G8550629448          GEAR SHAFT      CONT                    CESSNA206   U206G       2073356CE  CONT  O550  IO550F      17042SO  HARTZLHCJ3Y PHCJ3YF1    GL  ENGINE          SHEARED         D      E   ENGINE SHUTDOWN                                                                                 O  OTHER                                                                         TXTAXI/GRND HDL  1                      NM089QCUI404                    U20606373   679590                      DURING PREFLIGHT, ENGINE RUNUP PILOT WAS UNABLE TO CYCLE PROP AND THEN NOTICED ZERO OIL PRESSURE ON THE OIL PRESSURE GAUGE, ENGINE SHUTDOWN.  INSPECTION REVEALED THE GEAR SHAFT ASSY IN THE OIL PUMP HOUSING WAS SHEARD.  MFG HAS ASKED US TO SEND THE ENGINE BACK TO THE FACTORY FOR EXAMINATION.  WE HAVE PHOTOS OF THE FAILED PART IF YOU TELL US HOW TO SEND THEM TO YOU.                                                                                                                                                                                                                                                                                                                                                                  1H71 3O3  O  A4CE    E3SO    5  CP36EA    
20061115002982006111500298CE  2006       11         15         EVGR1113735      120061109G5310                DOOR FRAME                              BEECH 90    65A901      1152901CE  PWA   PT6   PT6A20      52043EA                              BS 255          CORRODED        B  EVGRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO3365JA 13353173               LM34                                    CORROSION WAS FOUND AT THE AFT DOOR FRAME AT FUSELAGE STATION 255.5 JUST BELOW AND OUT BOARD OF THE DOOR SNUBBER MOUNT.  DAMAGE WAS REPAIRED IAW SIRM PN 9839006C, DATED MARCH 2003, ATA 20-10-03 FIGURE 202, PAGES 204 AND 205 AND ATA 20-10-34, FIGURE 201, PAGES 201 AND 202.                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L72 3T3  T  3A20    E4EA                 
20060922000712006092200071EA  2006       9          22         EVGR20060915     220060913G7414103571651       COIL                                    ROBSINR44   R44         7640120WP  LYC   O540  O540F1B5    41532EA                              MAGNETO         WORN            B  EVGRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO33628PM498        E04JA347    1493        L2642740A                   DURING THE FIRST 500 HOUR MAGNETO INSPECTION, THE TAB ON THE COIL WAS MISALIGNED AND EXHIBITED EXCESSIVE WEAR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1G71 3O3  O  H11NM   E295                 
20060512000312006051200031GL  2006       5          12         EY2R0079965      320060421G6114E71693          HUB                                     BEECH 58    58P         1152744CE                                   HARTZLHCJ3Y PHCJ3YF2    GL  PROPELLER       CORRODED        B  EY2RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03                                                                    CORROSION ON PROPELLER HUB.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L72 3O      A23CE           5  CP36EA    
20060718001772006071800177CE  2006       7          18         FAA0607001       120060627G531212534095        FIREWALL                                CESSNA210   210K        2073446CE  CONT  O550  IO550*           SO  MCAULYD3A34 D3A34C402   GL  ZONE 100        CRACKED         B      K   NONE                                                                                            P  NO WARNING INDICATION                                                         ININSP/MAINT     1                      SW178142G6980                   21059442    289152R     931755          WHILE UNDERGOING AN ANNUAL INSPECTION THE ENGINE FIREWALL WAS FOUND TO BE CRACKED WHERE THE EXHAUST HANGER BRACKETS ATTACH ON THE LT SIDE. ADDITIONAL CRACKING WAS ALSO FOUND ON THE INNER BULKHEAD.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H71 3O3  O  3A21    E3SO    5  CP47GL    
20060718001782006071800178CE  2006       7          18         FAA0607002       120060627G531212534095        FIREWALL                                CESSNA210   210K        2073446CE  CONT  O550  IO550*           SO  MCAULYD3A34 D3A34C402   GL  ZONE 100        CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW178142G6980                   21059442    289152R     931755          WHILE UNDERGOING AN ANNUAL INSPECTION THE ENGINE FIREWALL WAS FOUND TO BE CRACKED WHERE THE EXHAUST HANGER BRACKETS ATTACH ON THE LT SIDE. ADDITIONAL CRACKING WAS ALSO FOUND ON THE INNER BULKHEAD.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H71 3O3  O  3A21    E3SO    5  CP47GL    
20070108003082007010800308CE  2007       1          8          FAA061214001     120061214G3230963800225       MOTOR                                   BEECH 95    D95A        1153408CE  LYC   O360  IO360A1A    41514EA                              LAND GEAR       SHORTED         B      A   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      CE038950U4094 164               TD641                                   LANDING GEAR MOTOR CIRCUIT BREAKER BLEW WHEN GEAR WAS RETRACTED ON TAKEOFF. AT THE SAME TIME THE ALTERNATORS DROPPED OFFLINE.  PILOT SWITCHED TO THE OTHER VOLTAGE REGULATOR AND THE ALTERNATORS CAME BACK ONLINE.  AIRCRAFT WAS FLOWN FOR AN HOUR OR MORE TO BURN OFF FUEL. PRIOR TO LANDING.  AN EMERGENCY WAS DECLARED.  PILOT WAS ABLE TO CRANK THE GEAR DOWN AND LAND WITHOUT INCIDENT. DISCOVERED THAT THE FIELD IN THE EXTEND SIDE OF THE LANDING GEAR MOTOR WAS SHORTED.  REPLACED MOTOR WITH OVERHAULED EXCHANGE PART. FUNCTIONALLY CHECKED OK.                                                                                                                                                                                        1L72 3O3  O  3A16    1E10                 
20061012000062006101200006CE  2006       10         12         FAA1012001       120061007G2800                FUEL                                    CESSNA182   T182T       2072738CE                                                               UNKNOWN         LEAKING         P      A   UNSCHED LANDING                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  CLCLIMB          1                      SW996004S                       T18208508                               AFTER AN APPROXIMATELY 30 MILE UNEVENTFUL FLIGHT WITH A LANDING AND TAXIBACK FOR DEPARTURE AT HVN THE AIRCRAFT WAS CLEARED FOR TAKEOFF BY THE TOWER.  THERE WAS A FEW MINUTES OF HOLDING PRIOR TO BEING RELEASED.  ON TAKEOFF FROM HVN RWY 2, THE AIRCRAFT FUNCTIONED NORMALLY UNTIL THE FIRST POWER REDUCTION AT 700 FEET AGL.  THE THROTTLE, PROP AND MIXTURE CONTROLS WERE FULL FORWARD.  THE PRIVATE PILOT ON BOARD PULLED THE THROTTLE BACK TO REDUCE THE TAKEOFF MANIFOLD PRESSURE FROM 32 TO 25 INCHES.  DURING THIS REDUCTION, THE ENGINE LOST POWER, SURGED BRIEFLY AND LOST POWER AGAIN.  THE THROTTLE APPEARED TO HAVE BEEN RETARDED SLOWLY AND CORRECTLY FOR THE EXPECTED POWER REDUCTION.  THE THROTTLE WAS ADVANCED AND NO POWER B1H71 3O    NT3A13                         
20061012000762006101200076    2006       10         12         FAA1012002       420060926G6113                BALANCE WEIGHT                          CESSNA177   177RG       2073709CE  LYC   O360  AEIO360A1B6 41514EA  MCAULY2D34C B2D34C208   GL  SPINNER         TORN            C      A   UNSCHED LANDING                                                                                 E  VIBRATION/BUFFET                                                              CRCRUISE         1                      WP27177SD10   10                177RG0997                               PROPELLER WAS BALANCED IN PLACE.  10 FLIGHT HOURS LATER, IN CRUISE OVER WYOMING EN ROUTE TO OSHKOSH, SIGNIFICANT VIBRATION OCCURRED, CAUSING DIVERSION TO THE NEAREST AIRPORT.  UPON LANDING, BYSTANDERS RAN TOWARD THE AIRPLANE TO EFFECT RESCUE, ASSUMING THE AIRPLANE TO BE ON FIRE FROM THE LARGE CLOUDS OF SMOKE.  BALANCE WEIGHTS HAD BEEN ATTACHED BY SCREW RADIALLY INSIDE THE SPINNER BACKING PLATE.  THE WEIGHTS (THREE WASHERS ON ONE SCREW) HAD PULLED THROUGH THE ALUMINUM OF THE BACKING PLATE, AND THE RESULTANT PROJECTION DAMAGED THE COWL MOUNT SYSTEM AND COWLING, AS WELL AS THE BACKING PLATE, AND SEPARATION OF THE BALANCE WEIGHTS.  THE IMBALANCE CREATED BY THIS TEARING OF THE BACKING PLATE CAUSED SEVERE VIBRATION, 1H71 3O3  O  A20CE   1E10    5  CP7EA     
20061020000982006102000098SW  2006       10         20         FAA1020001       120060921G28233610021         SELECTOR VALVE                          MOONEYM20   M20R        5870225SW  CONT  O550  IO550G      17042SO  HARTZLHCJ3Y PHCJ3YF1    GL  COCKPIT         STUCK           D      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      EA07533LJ71                     290443      688726      FP4606B         FUEL SELECTOR VALVE STUCK IN (OFF) POSITION WHILE AIRCRAFT WAS SITTING ON THE RAMP.  ONCE STUCK IN THE OFF POSITION, IT BECAME IMPOSSIBLE TO TURN USING HAND FORCE.  (K)                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L71 3O3  ORT2A3     E3SO    5  CP36EA    
20061025000872006102500087EA  2006       10         25         FAA1023001       220061013G8520                EXHAUST VALVE                           PIPER PA28  PA28140     7102802SO  LYC   O320  O320*       41508EA                              ENGINE          SEPARATED       D      A   UNSCHED LANDING                                                                                 Y  ENGINE STOPPAGE                                                               CRCRUISE         1                      CE075292S                       2826923                                 PILOT REPORTED ENGINE VIBRATION FOLLOWED BY PROGRESSING LOSS OF POWER WHICH EVENTUALLY LED TO COMPLETE LOSS OF POWER AND ENGINE FAILURE.  PILOT EXECUTED AN UNEVENTFUL EMERGENCY LANDING ON A PAVED STATE HIGHWAY.  NO DAMAGE TO AIRCRAFT UPON LANDING. RESULTS OF ENGINE EXAMINATION AND PARTICULAR PART FAILURE INFORMATION TO FOLLOW:                                                                                                                                                                                                                                                                                                                                                                                                        1L71 3O3  O  2A13    E274                 
20061031001442006103100144NM  2006       10         31         FAA1031001       120061027G5522                SKIN                                    ISRAEL1125  1125               NM  ALIDSGTFE731TFE7313AR        WP                              ELEVATOR        DELAMINATED     B  G7QRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP0771FS 4861                   071                                     DEBOND AREA APPROX. 7 IN X 7 IN ON THE RT OB ELEVATOR LOWER COMPOSITE SKIN. ELEVATOR WAS SENT TO MFG FOR EVALUATION AND WAS DEEMED (BEYOND ECONOMICAL REPAIR).  A LOANER UNIT WAS INSTALLED WHILE NEW/EXCHANGE UNIT PREPARED. REPLACEMENT ELEVATOR INSTALLED ON THIS DATE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F4  FRTA16NM   E6WE                 
20060821000822006082100082    2006       8          21         FAA200608001     120060609G32440398561         TIRE                                                                                                                                    MLG             SEPARATED       B      C   ABORTED TAKEOFF                                                                                 S  AFFECT SYSTEMS                                                                TOTAKEOFF        1                      SO250874                                                                LOUD BANG REPORTED BY PILOTS RESULTING IN REJECTED TAKE-OFF. MAINT FOUND  DAMAGE TO ENGINE FROM TIRE.  SHOP INVESTIGATION REVEALED, TIRE TREAD SEPARATED FROM CARCASS.  NO LEAKAGE FROM WHEEL.  PASSED AIR RETENTION AFTER 167 HOURS WITH ACCEPTABLE AIR LOSS FROM WHEEL SERIAL NUMBER 01466.  CAUSE IS UNDETERMINED TO WHY TREAD SEPARATED, TIRE TO BE SENT TO MICHELIN FOR TIRE INVESTIGATION.                                                                                                                                                                                                                                                                                                                                                                                          
20061207002452006120700245SO  2006       12         7          FAA200612001     220061206G8530                CYLINDER                                CESSNA421   421C        2076016CE  CONT  O520  GTSIO520L   17032SO                                              SEPARATED       B      C   ABORTED TAKEOFF                                                                                 RJ PARTIAL RPM/PWR LOSS      WARNING INDICATION                                  TOTAKEOFF        1                      WP2393PJ      554               421C0824    245999R                     DURING TAKEOFF ROLL PILOT REPORTED A LOUD POP FROM THE LEFT ENGINE AND THE AIRCRAFT YAWED TO THE LEFT. THE TAKEOFF WAS ABORTED. VISUAL INSPECTION REVEALED THE NUMBER SIX CYLINDER HEAD HAD SEPARATED FROM THE BARREL. THE ENGINE HAD 554 HOURS SINCE OVERHAUL. THIS ENGINE WAS INSTALLED ON A CESSNA 421C.                                                                                                                                                                                                                                                                                                                                                                                                                                     1L72 3O3  O  A7CE    E7CE                 
20061012000132006101200013    2006       10         12         FAA63837         420061003G6113D78115P         SPINNER                                                                                                     HARTZLHCJ3Y PHCJ3YF2    GL  PROPELLER       CRACKED         B      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL2558HW 102                                            ED4696B         RT PROPELLER SPINNER CRACKED.  CRACKS ORIGINATE FROM 1ST SCREW HOLE ADJACENT TO BLADE OPENING.  THIS IS THE 2RD OCCURANCE OF THIS DEFECT.  PROBABLE CAUSE UNKNOWN.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           5  CP36EA    
20060926000442006092600044GL  2006       9          26         FASD0601         120060904G5210                ROLLER                                  BOMBDRBD700 BD7001A10   1390006GL                                                               PAX DOOR        OUT OF ADJUST   B      A   UNSCHED LANDING                                                                                 O  OTHER                                                                         CLCLIMB          1                      GL15889CP                       9104                                    AFTER TAKE-OFF AIRCRAFT CABIN WOULD NOT PRESSURIZE. AIRCRAFT RETURNED TO  AIRPORT WITHOUT INCIDENT.  INVESTIGATION BY GROUND CREW FOUND REAR BAGGAGE DOOR MISALIGNED AND AFT ROLLER OUT OF GUIDE TRACK AND REAR LOCKING PIN NOT FULLY ENGAGED, ALL INDICATIONS IN THE COCKPIT WERE NORMAL AS SENSORS ARE FITTED TO FRONT PIN AND DOOR LOCKING MECHANISM ONLY. DOOR WAS RE-FITTED INTO THE TRACK CORRECTLY, DOOR SECURED CLOSED NORMALY, AIRCRAFT DEPARTED AND FLIGHT CONTINUED WITHOUT INCIDENT.                                                                                                                                                                                                                                                2L72 4F    RTT00003NY                     
20070108001712007010800171NE  2007       1          8          FCPR20060026     220061213G720065526022        RING                                    CESSNA500   560CESSNA   2076750CE  PWA   530   PW535A           NE                              RT ENGINE       CRACKED         B  FCPRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM09591DK940  300               5600591                                 RT ENGINE INLET SUPPORT RING CRACKED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F4  FRTA22CE   E00053EN             
20070108002172007010800217CE  2007       1          8          FCPR20060027     120061215G3830105881          HEATER                                  CESSNA525   525A        2076615CE  WILINTFJ44  FJ44        66000GL                              ZONE 100        BURNED          B  FCPRO   OTHER                                                                                           A  FLAME/FIRE                                                                    TXTAXI/GRND HDL  1                      NM09523BT1247 300               525A0124                                AFT TOILET RELIEF TUBE HEATER ELEMENT FAILED WITH EXTERNAL POWER APPLIED BURSTING INTO FLAMES.  IPC REFERENCE 38-30-00 FIG 3 ITEM 16.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L71 4F4  FRTA1WI    E3GL                 
20060829001332006082900133CE  2006       8          29         FCPR20060030     120060822G79311013890237      TRANSMITTER                             BEECH 300   300BEECH    1152930CE                                                               LT ENGINE       FAILED          B  FCPRE   ENGINE SHUTDOWN                                                                                 N  FALSE WARNING                                                                 CRCRUISE         1                      NM09528AM4273                   FA59                                    LT ENGINE OIL PRESSURE TRANSMITTER FAILED, GIVING A LOW OIL PRESSURE INDICATION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4T      A24CE                        
20060510002372006051000237    2006       5          10         FCPR20060050     420060509G22114008519         COMPUTER                                CESSNA500   S550        2076607CE                                                               COCKPIT         FAILED          B  FCPRO   OTHER                                                                                           S  AFFECT SYSTEMS                                                                NRNOT REPORTED   1                      NM09543SC6347                   S5500144                                AUTOPILOT COMPUTER FAILED CAUSING PILOTS ALTIMETER/AIRDATA COMPUTER TO FAIL.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    1L72 4F    RTA22CE                        
20060511002902006051100290CE  2006       5          11         HAG06002         120060406G531325FN86          LONGERON                                RAYTHNDH125 DH125       4230106CE                                                               FUSELAGE        CRACKED         B  J7EAK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM03125CK10555                  25266                                   CRACK IN KEEL LONGERON BETWEEN FRAMES 4 AND 5, APROXIMATE STATION 175.00.CRACK IS ONLY IN LONGERON, NOT IN MAIN BEAM.  CRACK LOCATED IN LOWER AFT HOLE FOR NOSE GEAR ATTACH BRACKET.  DISCOVERED DURING REQUIRED CHECK OF ATTACH BOLT TORQUE, ALL BOLTS FOUND LOOSE.  BRACKET REMOVED FOR HIDDEN DAMAGE INSPECTION.                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4J    RTA3EU                         
20061117001392006111700139NE  2006       11         17         HL01102006001    120061031G6320SB24102         BEARING         SKRSKY                  SKRSKYS64   CH54A       8142501NE                                                               M/R GEARBOX     FAILED          C      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      WP23          357   77          6818447                                 MAIN GEAR BOX BEGAN MAKING METAL, THIS WAS NONFERROUS METAL, UPON REMOVAL AND DISASSEMBLY IT WAS DISCOVERED THAT THE 1ST STAGE PLANETARY BEARING, P/NSB2410-2 HAD FAILED, BEARING WAS REPLACED AND RETURNED TO SERVICE.  FOR FURTHER INFO SEE HEAVY LIFT WORK ORDER NR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2G72 4U      H16NM                        
20070108001462007010800146    2007       1          8          HN8R200600001    420061207G2200065001782400    SERVO                                   GIPPLDGA8   GA8         3900102EU  LYC   O540  IO540K1A5   41532EA                              AUTOPILOT       DEFECTIVE       B  HN8RC   ABORTED TAKEOFF                                                                                 O  OTHER                                                                         TOTAKEOFF        1                      CE05576GA1    1                 05076                                   NOSE DOWN AUTO TRIM INOP WAS REPORTED BY PILOT.  TROUBLESHOOTING REVEALED THE AUTOPILOT COMPUTER WAS NOT RECEIVING INPUT CALLING FOR NOSE DOWN TRIM FROM THIS PITCH SERVO.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1H71 3O3  ONT        1E4                  
20070108002212007010800221EA  2007       1          8          HN8R200700001    220061223G8550                SCREEN                                  GIPPLDGA8   GA8         3900102EU  LYC   O540  IO540K1A5   41532EA                              ENGINE OIL SUMP CONTAMINATED    B  HN8RK   NONE                                                                                            J  WARNING INDICATION                                                            ININSP/MAINT     1                      CE05576GA219                    GA805076    L3033548A                   FOUND 2 PIECES OF METAL IN THE OIL SUMP SUCTION SCREEN DURING ANNUAL INSPECTION.  ONE PIECE LOOKS LIKE A DRILLED OUT HELI COIL .5 INCH LONG X .25 WIDE AND THE OTHER LOOKS LIKE A PIECE OF CASTING .2 LONG X .125 WIDE.  THE ENGINE WILL BE REMOVED AND SENT OUT FOR TEARDOWN AND INSPECTION.                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H71 3O3  ONT        1E4                  
20061115002122006111500212CE  2006       11         15         IALFAASDR1       120061103G2430                WIRE HARNESS                            BEECH 58    58          1152740CE  CONT  O520  IO520*      17032SO                              AIR DRIVEN GEN  BROKEN          H      K   NONE                                                                                            G  MULTIPLE FAILURE                                                              ININSP/MAINT     1                      SO05302P                        TH952                                   AIR DRIVEN GENERATOR TEST IN FLIGHT, FOUND NO OUTPUT.  FOUND WIRING HARNESS FROM ADG TO ADG BUSS BURNED-BROKEN AT CONNECTOR BACKSHELL.  CONNECTOR AND WIRING REPLACED ADG INSPECTED AND TESTED SERVICEABLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L72 3O3  O  3A16    E5CE                 
20060512000792006051200079CE  2006       5          12         IGL032006007     120060329G3222084200077       STRUT           CESSNA                  CESSNA310   310K        2074228CE  CONT  O470  IO470*      17026SO                              NLG             FAILED          G      A   UNSCHED LANDING                                                                                 K  FLUID LOSS                                                                    LDLANDING        1                      GL037035L                       310K0135                                NOSE GEAR STRUT ASSEMBLY COLLAPSED DURING EITHER TAXI OR TAKEOFF.  WHEN GEAR WAS RETRACTED THE NOSE FENDER CAUGHT ON THE GEAR DOOR BRACKETS.  MOTOR CONTINUED UNTIL IDLER BELLCRANK BROKE.  AIRCRAFT MADE AN EMERGENCY LANDING WITH THE NOSE GEAR COLLAPSED.  PILOT REPORTED NO ABNORMAL OBSERVATIONS OF THE NOSE GEAR DURING PREFLIGHT INSPECTION.  IT IS NOT UNCOMMON FOR THE STRUT TO BLOW THE SEALS AND LOOSE ALL OF ITS FLUID AND NITROGEN DURING COLD WEATHER.  LOW UTILIZATION MIGHT HAVE BEEN A CONTRIBUTING FACTOR AS WELL.                                                                                                                                                                                                            1L72 3O3  O  3A10    E1CE                 
20060411000312006041100031CE  2006       4          11         ISW1520050019    120060223G8000643359K46       ADAPTER                                 CESSNA421   421C        2076016CE  CONT  O520  GTSIO520N   17032SO                              STARTER         FAILED          G      O   OTHER                                                                                           Y  ENGINE STOPPAGE                                                               CRCRUISE         1                      SW15421LH714                    421C1207    808393                      THE ENGINE QUIT RUNNING AND SEIZED DURING FLIGHT. THE STARTER ADAPTER FAILED AND CAUSED THE ENGINE TO SEIZE.  MAINTENANCE RECORDS SHOW THAT THE STARTER WAS REPLACED TWO TIMES BECAUSE OF HARD STARTING.  ONCE AT 99 HOURS AND AGAIN AT 90 HOURS PRIOR TO ENGINE FAILURE                                                                                                                                                                                                                                                                                                                                                                                                                                                                        1L72 3O3  O  A7CE    E7CE                 
20070109000012007010900001CE  2007       1          9          JEMA11302006A    120061130G5610991438010       WINDSHIELD                              CESSNA500   560CESSNA   2076750CE  PWA   545   PW545A           NE                              COCKPIT         CRACKED         G  JEMAA   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CRCRUISE         1                      CE01108EK2662                   5605032                                 AIRCRAFT HAD DEPARTED, HAD LEVELED OFF AT 37,000 FEET, ENROUTE. CREW NOTICED A RT WINDSHIELD FAULT WARNING LIGHT. IAW AFM PROCEDURES RT WINDSHIELD HEAT WAS TURNED OFF. APPROX 3-4 MINUTES LATER CO-PILOT SAW FLASH AND RT WINDSHIELD SPIDER WED CRACKED.  FLIGHT CREW MADE A PRECAUTIONARY LANDING AT AIRPORT, WITH NO FURTHER INCIDENTS.                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F4  FRTA22CE   E00059EN             
20060718001642006071800164CE  2006       7          18         LJCR2453796      120060301G302045A403041       DUCT                                    BEECH MU300 400A        1155402CE                                                                               OUT OF LIMITS   B  LJCRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW09999JF                       RK98                                    DURING SCHEDULED MAINTENANCE, FOUND BRAIDING AROUND FLEXIBLE BELLOWS DISBONDED FROM ENTIRE CIRCUMFERENCE.  NEW REPLACEMENT DUCT ASSEMBLIES NOT AVAILABLE FROM MANUFACTURER.  REPLACED WITH SERVICEABLE UNIT.  INSPECTED REPLACEMENT UNIT PER AD 2001-03-06 EFF. 3-21-2001                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2H72 4F    RTA16SW                        
20061117001592006111700159GL  2006       11         17         LX5R200600002    320061115G6197K31C22          WIRE HARNESS    BEECH                   BEECH B300  B300        1159232CE  PWA   PT6   PT6A60A     52043NE  HARTZLHCB4M HCB4MP3     GL  AUTOFEATHER SYS SHORTED         C  LX5RC   ABORTED TAKEOFF                                                                                 J  WARNING INDICATION                                                            TOTAKEOFF        1                      GL19961LL3310                   FL264                                   UPON TAKEOFF ROLL THE CREW GOT THE AUTOFEATHER OFF LIGHT AND THE MASTER CAUTION LIGHT. THE CREW THEN OPTED TO ABORT TAKEOFF ROLL AND RETURN TO RAMP WITHOUT INCIDENT. UPON RETURNING TO RAMP THE CREW NOTICED THAT THE AUTOFEATHER CIRCUIT BREAKER HAD POPPED, IT WAS RESET BUT WOULD POP AGAIN UPON PUSHING THE LT POWER LEVER FORWARD. THE PLANE WAS BROUGHT INTO MAINTENANCE AND THE MECHANIC FOUND THAT THERE WAS A CHAFED WIRE BEHIND THE INSTRUMENT PANEL FOR THE AUTOFEATHER SWITCH. THIS WIRE WAS REPAIRED AND THE AIRCRAFT WAS OPS CHECKED AND RETURNED TO SERVICE.                                                                                                                                                                    2L72 4T4  TRTA24CE   E4EA    6  CP56GL    
20061212003982006121200398    2006       12         12         LX5R200600003    320061115G6197K31C22          WIRE HARNESS                            BEECH B300  B300        1159232CE  PWA   PT6   PT6A60A     52043NE                              COCKPIT         SHORTED         B  LX5RC   ABORTED TAKEOFF                                                                                 J  WARNING INDICATION                                                            TOTAKEOFF        1                      GL19961LL3310                   FL264                                   UPON TAKEOFF ROLL, THE CREW GOT THE AUTO FEATHER OFF LIGHT AND THE MASTER CAUTION LIGHT.  THE CREW THEN OPTED TO ABORT TAKEOFF ROLL AND RETURN TO RAMP WITHOUT INCIDENT.  UPON RETURNING TO RAMP, THE CREW NOTICED THAT THE AUTO FEATHER CRICUIT BREAKER HAD POPPED, IT WAS RESET BUT WOULD POP AGAIN UPON PUSHING THE LT POWER LEVER FWD.  THE PLANE WAS BROUGHT INTO MAINTENANCE AND THE MECHANIC FOUND THAT THERE WAS A CHAFED WIRE BEHIND THE INSTRUMENT PANEL FOR THE AUTOFEATHER SWITCH.  THIS WIRE WAS REPAIRED AND THE AIRCRAFT WAS OPS CHECKED AND RETURNED TO SERVICE.  (K)                                                                                                                                                           2L72 4T4  TRTA24CE   E4EA                 
20060518001722006051800172SO  2006       5          18         MPVMANIFOLD      220060328G732463432612A2      FUEL DIVIDER                            CESSNA206   TU206G      2073357CE  CONT  O520  TSIO520M    17040SO                              ENGINE          LEAKING         D      K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      WP21PKMPV98                     U20605864   532289                      FUEL MANIFOLD VALVE IS LEAKING FROM THE VENT PORT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              1H71 3O3  O  A4CE    E8CE                 
20060530001562006053000156CE  2006       5          30         N6265B           120060524G5312125340956       BULKHEAD        CESSNA                  CESSNA210   210M        2073450CE                                                               FIREWALL        CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW176265B4908                   21062727                                WHILE UNDERGOING AN ANNUAL INSPECTION, FOUND THE FIREWALL TO BE CRACKED ON THE LT & RT SIDE WHERE THE P/N 1250255-7 EXHAUST HANGAR BRACKETS ATTACH. THE CRACKS WERE EXTENDING OUT FROM UNDER THE HANGAR BRACKETS AND EXTENDED IN MULTIPLE DIRECTIONS. ADDITIONAL INSPECTION REVEALED THE LT BULKHEAD P/N 1253409-5 AND RT BULKHEAD P/N 1253409-6 BEHIND THE FIREWALL TO BE CRACKED IN MULTIPLE DIRECTIONS ALSO. THE BULKHEAD SECTIONS WERE REPLACED AND THE FIREWALL CRACKS WERE REPAIRED.                                                                                                                                                                                                                                                      1H71 3O      3A21                         
20060718001762006071800176CE  2006       7          18         N8142G           120060627G531212534095        FIREWALL                                CESSNA210   210K        2073446CE  CONT  O550  IO550*           SO  MCAULYD3A34 D3A34C402   GL  FUSLEAGE        CRACKED         D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW178142G6980                   21059442    289152R     931755          WHILE UNDERGOING AN ANNUAL INSPECTION THE ENGINE FIREWALL WAS FOUND TO BE CRACKED WHERE THE EXHAUST HANGER BRACKETS ATTACH ON THE LT SIDE. ADDITIONAL CRACKING WAS ALSO FOUND ON THE INNER BULKHEAD.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1H71 3O3  O  3A21    E3SO    5  CP47GL    
20060914001622006091400162CE  2006       9          14         NA               120060822G52803511513022      ANGLE                                   BEECH 36    A36         1151604CE                                                               MLG DOOR        CRACKED         C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL19     360                    E3384                                   DURING A ROUTINE ANNUAL INSPECTION IT WAS FOUND THAT BOTH THE LT AND RT IB GEAR DOOR AFT HINGE ANGLES (P/N'S 35-115130-22, -24, 35-115070-16 AND -18 WERE CRACKED.  IT IS MY OPINION THAT THIS IS DUE TO THE FACT THAT MFG HAS CHANGED THE DESIGN OF THE IB GEAR DOOR FROM A STAMPED ASSY TO A MILLED PART.  THIS CONDITION OBVIOUSLY IS PRESENT IN OTHER LIKE MODELS AND MFG HAS ACKNOWLEDGED THE PROBLEM IN THEIR PARTS BOOK AS THEY GIVE INSTRUCTIONS FOR ORDERING DIFFERENT PN.  THE NEW PN PARTS ARE MADE FROM .050 INCH ALUMINUM WHILE THE ORIGINAL PARTS WERE MADE FROM .032 INCH ALUMINUM. THE CRACKS COULD EASILY GO UNDETECTED AND A SB IS NEEDED TO HELP OTHERS FIND AND ELIMINATE THESE CRACKS.                                     1L71 3O      3A15                         
20060518001352006051800135CE  2006       5          18         OMKR200600002    120060509G551145A21104642     RIB                                     BEECH MU300 400A        1155402CE                                                               ZONE 300        CRACKED         B  OMKRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM03899TA4933                   RK292                                   CRACKED ROLLER RIB ASSEMBLY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    2H72 4F    RTA16SW                        
20060516000902006051600090CE  2006       5          16         OMKR200600003    120060510G551445A21104641     RIB                                     BEECH MU300 400A        1155402CE                                                               HORIZ STAB      CRACKED         B  OMKRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM03686TA                       686TA                                   CRACKED ROLLER RIB SUPPORT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2H72 4F    RTA16SW                        
20060718000972006071800097CE  2006       7          18         OMKR20064        120060712G57405012007378      FITTING                                 BEECH 90    65A90       1152908CE                                                               WING SPAR       CRACKED         B  OMKRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      NM0366GS 11099                  LJ237                                   DURING ACCOMPLISHMENT OF AD 89-25-10, BOTH THE FOREWARD, LOWER, INBOARD, BATHTUB FITTINGS WERE FOUND WITH TWO EACH 1/4" CRACKS.  THE FEATHERED EDGE CRACKS EXTENDED INTO THE BOLT HOLE RADIUS, AND THE SLOT CRACKS EXTENDED UPWARD. BOTH FITTINGS WERE CRACKED VIRTUALLY THE SAME.  PARTS WERE REPLACED WITH NEW.                                                                                                                                                                                                                                                                                                                                                                                                                               1L72 3T      3A20                         
20060510002422006051000242CE  2006       5          10         PAI5200604049    120060417G32427540            PLATE           CLEVELAND               BEECH 95    95B55       1152729CE                                                               RT BRAKE        CRACKED         B  PAI5K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO056747V3103                   TC2316                                  DURING ANNUAL INSPECTION FOUND RT BRAKE TORQUE PLATE CRACKED .7500 OF THE LENGTH OF THE CALIPER PIN BORE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1L72 3O    RT3A16                         
20060721001402006072100140EU  2006       7          21         PAI5200641881    120060628G554080363216801     STOP                                    PIAGIOP180  P180        6960204EU                                                               RUDDER          BROKEN          B  PAI5K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05153SL2966                   1054                                    DURING D CHECK (3000 HOUR INSPECTION) FOUND RUDDER STOP LOCATED AT BOTTOM OF RUDDER BROKEN IN TWO.  BREAK OCCURRED AT SCREW HOLES USED TO ATTACH WEAR STRIP TO RUDDER STOP.  SMALL AREA OF METAL EXISTS AROUND THE SCREW HOLES, SUGGEST REDESIGN OF THIS PART.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  1H72 3O    RTA59EU                        
20060926000272006092600027NE  2006       9          26         PAI5200642401    220060825G72613040124         LINE                                    PIAGIOP180  P180        6960204EU  PWA   PT6   PT6A66      52043NE                              OIL COOLER      CHAFED          B  PAI5K   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      SO05153SL2989                   1054        PCERK0064                   DURING 3000 HOUR D-CHECK FOUND OIL SCAVENGE LINE PN 3040124 AT SCAVENGE PUMP CHAFED APPROX 50 PERCENT THROUGH BY CONTACT WITH CRIMP TYPE CLAMP THAT SECURES HEAT SLEEVE ON OIL COOLER FLEX LINE.  SAME CONDITION FOUND ON BOTH LT AND RT ENGINES.  INSTALLED NEW SCAVENGE LINE BOTH ENGINES.                                                                                                                                                                                                                                                                                                                                                                                                                                                    1H72 3O4  TRTA59EU   E26NE                
20060913001032006091300103EU  2006       9          13         PAI5200642731    120060901G301080232118401     DUCT            PIAGIO                  PIAGIOP180  P180        6960204EU                                                               WING            CRACKED         B  PAI5K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05107SL2993                   1073                                    DURING 3000 HOUR D-CHECK FOUND ALL 4 WING LEADING EDGE PANELS WITH CRACKED HEATING DUCTS.  WING LEADING EDGE ASSY P/N'S 80-232116-401, 80-232116-402, 232117-401, 232117-402.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1H72 3O    RTA59EU                        
20060627003312006062700331EU  2006       6          27         PAI52006S4188    120060622G301080237666403A    TUBE                                    PIAGIOP180  P180        6960204EU                                                               ANTI ICE SYS    CHAFED          B  PAI5K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05153SL2966 2966              1054                                    DURING D-CHECK (3000 HOUR INSPECTION) FOUND WING LEADING EDGE ANTI-ICE PLUMBING CHAFFED 50 PERCENT OF WALL THICKNESS BY LEADING EDGE TEMP SENSOR BRACKET.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       1H72 3O    RTA59EU                        
20060802003062006080200306SO  2006       8          2          PAI52006S4248    120060726G2823                CONTROL CABLE                           PIPER PA23  PA23250     7102308SO                                                               FUEL SELECTOR   BROKEN          B  PAI5A   UNSCHED LANDING                                                                                 X  ENGINE FLAMEOUT                                                               CRCRUISE         1                      SO0518MW                        27369                                   PILOT REPORTED LT ENGINE QUIT IN FLIGHT.  FOUND LT OB FUEL TANK EMPTY, LT IB FUEL TANK HAD FUEL.  FOUND FUEL SELECTOR CONTROL CABLE BROKEN AT SELECTOR VALVE IN LT NACELLE.  WHEN SELECTED TO LT IB TANK THE ENGINE RAN NORMALLY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               1L72 3O      1A10                         
20061031001632006103100163CE  2006       10         31         PAI52006S4330    120061025G3246300257          WHEEL                                   BEECH 90    C90A        1152911CE                                                               MLG             CRACKED         B  PAI5K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05511KV3500                   LJ1422                                  PILOT NOTED RT MAIN TIRE LOW PRESSURE ON PREFLIGHT.  MAINTENANCE FOUND, UPON DISASSEMBLY OF WHEEL, THAT THE INNER WHEEL HALF WAS CRACKED IN THE O-RING GROOVE ADJACENT TO THE WHEEL TIE BOLT HOLES.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L72 3T    RT3A20                         
20060518001862006051800186EU  2006       5          18         PAZR200620412    120060428G3211MY201121605     PLUG            AMD                     AMD   FALC20FALCON20F5  2730105EU                                                               ZONE 700        CORRODED        B  PAZRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE03620A                        412                                     DURING THE COURSE OF REPLACING THE LT MLG ASSEMBLY, THE TECHNICIAN, UPON VISUAL INSPECTION AFTER REMOVAL OF MLG ASSY, FOUND SIGNS OF CORROSION ON THE PLUG, P/N MY20112-1605.  UPON FURTHER DISASSEMBLY, IT WAS NOTED THAT THE CORROSION HAD GONE THROUGH THE PLUG. THE SEALANT ON ONE SIDE OF THE PLUG WAS PREVENTING FUEL LEAKAGE.  PART WAS ORDERED FROM MFG AND REPLACED WITH A NEW PLUG, P/N MY20112-1605-1. IT APPEARS THAT THE NEW PLUG HAS A DIFFERENT DESIGN AND PAINT PROTECTION SYSTEM; THUS AIDING IN THE PREVENTION OF FUTURE CORROSION. THE AIRCRAFT WAS MFG. IN 1979.                                                                                                                                                            2L72 4F    RTA7EU                         
20060630000212006063000021NM  2006       6          30         PIDR2006001      120060608G5551                ATTACH FITTING                          BOEING737   73735B      13844BMNM                                                               HORIZ STAB      DAMAGED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05223DZ                       23972                                   DURING AN A-CHECK/BRIDGING CHECK FOR RETURN TO SERVICE FROM STORAGE, MAINTENANCE DISCOVERED A TIME LIMITED BLENDOUT REPAIR TO THE AFT FACE OF THE LEFT HORIZONTAL STABILIZER LOWER FORWARD ATTACH LUG.  REWORKED AFT FACE OF LOWER FORWARD ATTACH LUG PER DELTA ENGINEERING REPAIR/AUTHORIZATION 089066-14 REVISION D DATED 5/10/06 WITH FAA 8100-9 APPROVAL DATED 5/30/2006.                                                                                                                                                                                                                                                                                                                                                                   2L72 4F    RTA16WE                        
20060711000652006071100065NM  2006       7          11         PIDR2006002      120060608G5753                SKIN                                    BOEING737   73735B      13844BMNM                                                               TR FLAPS        CHAFED          B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05223DZ                       23972                                   INSPECTION NOTED A CHAFED AREA ON AN EXISTING SRM ALUMINUM REPAIR DOUBLER ON THE RIGHT WING OUTBOARD FLAP MID-FLAP LEADING EDGE 20 INCHES FROM THE INBOARD END.  REPAIRED DAMAGED AREA IN ACCORDANCE WITH PACE AIRLINES REPAIR PROCEDURE REPORT EA 57-145 DATED 05/25/06 WITH FAA DER APPROVAL FORM 8110-3 DATED MAY 30, 2006.                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F    RTA16WE                        
20060705000242006070500024NM  2006       7          5          PIDR2006003      120060608G5330                SKIN                                    BOEING737   73735B      13844BMNM                                                               FUSELAGE        DAMAGED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05223DZ                       23972                                   AN EXISTING REPAIR TO THE FUSELAGE SKIN BETWEEN THE L1 DOOR HINGES JUST FORWARD OF THE DOOR REQUIRES REWORK TO REMOVE THE DAMAGE.  REWORKED DAMAGED AREA IAW EA NR 53-146 DATED 05/26/06 WITH FAA DER APPROVED 8110-3 DATED MAY 27, 2006..                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F    RTA16WE                        
20060711000642006071100064NM  2006       7          11         PIDR2006004      120060608G5754                SKIN                                    BOEING737   73735B      13844BMNM                                                               NR 5 SLAT       CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05223DZ                       23972                                   INSPECTION NOTED A GOUGE ON THE NR 5 SLAT UPPER LEADING EDGE SURFACE 28 INCHES FROM THE INBOARD END (SS169.0).  REPAIRED DAMAGED AREA IN ACCORDANCE WITH PACE AIRLINES REPAIR PROCEDURE REPORT EA 57-140 DATED 05/20/06 WITH FAA DER APPROVED 8110-3 DATED MAY 20, 2006.                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F    RTA16WE                        
20060711000632006071100063NM  2006       7          11         PIDR2006005      120060608G5754                SKIN                                    BOEING737   73735B      13844BMNM                                                               NR 5 SLAT       CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05223DZ                       23972                                   INSPECTION NOTED CRACKS AT SEVERAL FASTENER LOCATIONS IN THE NR 5 SLAT LOWER TRAILING EDGE SKIN PANEL UNDER THE SLAT ACTUATOR.  REPAIRED DAMAGED AREA IN ACCORDANCE WITH SRM 57-43-01.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA16WE                        
20060711000622006071100062NM  2006       7          11         PIDR2006006      120060608G5754                SKIN                                    BOEING737   73735B      13844BMNM                                                               NR 3 SLAT       CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05223DZ                       23972                                   INSPECTION NOTED SEVERAL CRACKS IN THE NR 3 SLAT LOWER TRAILING EDGE SKIN BELOW THE SLAT ACTUATOR.  REPAIRED DAMAGED AREA PER SRM 57-43-01.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F    RTA16WE                        
20060627003332006062700333NM  2006       6          27         PIDR2006007      120060619G5330                SKIN                                    BOEING737   7373L9      1384470NM                                                               BS 887-907      DENTED          B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05231DN                       23717                                   DURING A-CHECK/BRIDGING CHECK FOR RETURN TO SERVICE FROM STORAGE, INSPECTION NOTED DENTS BEYOND ALLOWABLE LIMITS IN FUSELAGE SKIN FROM BS887 TO BS907 BETWEEN STR20RT AND STR22RT.  REPAIRED IAW SRM 53-00-01.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F    RTA16WE                        
20060630000192006063000019NM  2006       6          30         PIDR2006008      120060613G5330                SKIN                                    BOEING737   7373L9      1384470NM                                                               FUSELAGE        DENTED          B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05231DN                       23717                                   DURING A-CHECK/BRIDGING CHECK FOR RETURN TO SERVICE FROM STORAGE, INSPECTION NOTED A DENT IN THE FUSELAGE SKIN BEYOND ALLOWABLE LIMITS AT BS 887 STR 22 LT.  REPAIRED PER SRM 53-00-01.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F    RTA16WE                        
20060630000202006063000020NM  2006       6          30         PIDR2006009      120060606G5512                SKIN                                    BOEING737   7373L9      1384470NM                                                               HORIZ STAB      DAMAGED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05231DN                       23717                                   DURING A-CHECK/BRIDGING CHECK FOR RETURN TO SERVICE FROM STORAGE, DAMAGE NOTED ON THE RIGHT HORIZONTAL STABILIZER APPROXIMATELY 8 FEET FROM THE INBOARD END.  REPAIRED PER SRM 55-10-01.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F    RTA16WE                        
20060724000182006072400018NM  2006       7          24         PIDR2006010      120060717G5300                REPAIR                                  BOEING737   737330      13844BJNM                                                               FUSELAGE        IMPROPER        B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05241DL                       23833                                   EXISTING REPAIR AT BS887 AND STR25RT NOT IN COMPLIANCE WITH THE SRM.  REPLACED EXISTING REPAIR IAW SRM 53-00-01 REPAIR 31.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F    RTA16WE                        
20060831000922006083100092NM  2006       8          31         PIDR2006011      120060824G5754                SKIN                                    BOEING737   737330      13844BJNM                                                               L/E SLAT        CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05242DL                       23834                                   NUMBER THREE SLAT LOWER SKIN IS CRACKED AT THE ACTUATOR.  REPAIRED PER SRM 57-43-01.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F    RTA16WE                        
20060831000902006083100090NM  2006       8          31         PIDR2006012      120060826G5330                SKIN                                    BOEING737   737330      13844BJNM                                                               FUSELAGE        DENTED          B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05242DL                       23834                                   FUSELAGE SKIN DENTED FROM BS 867 TO BS 947 BETWEEN STR 21 RT AND 22 RT.  REPAIRED PER EA 53-220.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F    RTA16WE                        
20060831000892006083100089NM  2006       8          31         PIDR2006013      120060826G5313                STRINGER                                BOEING737   737330      13844BJNM                                                               FUSELAGE        DAMAGED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05242DL                       23834                                   STRINGER 19 LT AT BS 967 HAS TWO REPAIRS NOT PER THE SRM.  REPLACED SECTION OF STRINGER PER SRM 53-00-03 FIG 201, REPAIR 1 AND 51-40-2.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F    RTA16WE                        
20060831000912006083100091NM  2006       8          31         PIDR2006014      120060824G5320                STRUCTURE                               BOEING737   737330      13844BJNM                                                               FUSELAGE        DAMAGED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05242DL                       23834                                   DOUBLER UNDER THE L-2 DOOR AT BS 975 HAS NO DOCUMENTATION.  REPLACED EXISTING DOUBLER PER EA 53-221.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F    RTA16WE                        
20060913002392006091300239NM  2006       9          13         PIDR2006015      120060823G5711                SPAR                                    BOEING737   737330      13844BJNM                                                               WING            DAMAGED         B  PIDRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05242DL                       23834                                   DURING REPLACEMENT OF THE AFT OB SUPPORT FITTING FOR THE MAIN LANDING GEAR BEAM IAW SB 737-1216R2 PART III, NOTED SEVERAL ATTACHMENT HOLES IN SPAR CHORD AND WEB TO BE OUT OF ROUND.  REPAIRED DAMAGE IAW MFG MESSAGE NR 1-21375291-12 DATED 26 JULY 2006 AND FAA FORM 8100-9 DATED 7 AUG 2006 AS AN AMOC TO AD 2005-18-08.                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F    RTA16WE                        
20060913002382006091300238NM  2006       9          13         PIDR2006016      120060823G574365C365451       FITTING                                 BOEING737   737330      13844BJNM                                                               MLG             ELONGATED       B  PIDRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05242DL                       23834                                   DURING REPLACEMENT OF THE AFT OB SUPPORT FITTING FOR THE MAIN LANDING GEAR BEAM IAW SB 737-1216R2, PART III, NOTED SEVERAL ATTACHMENT HOLES IN THE REPLACEMENT FITTING OUT OF ROUND.  REPAIRED DAMAGE AREA IN FITTING IAW MESSAGE NUMBER 1-213752921-12 DATED 26 JUL 2006 AND FAA FORM 8100-9 DATED 7 AUG 2006 WHICH IS AN AMOC TO AD 2005-18-08.                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F    RTA16WE                        
20060913002662006091300266NM  2006       9          13         PIDR2006017      120060801G5711654532421       SPAR                                    BOEING737   737330      13844BJNM                                                               BS 224          DAMAGED         B  PIDRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05241DL                       23833                                   FASTENER HOLE IN THE LT UPPER REAR SPAR CHORD AT STA 224.14 (AT THE LANDING GEAR BEAM OB ATTACH FITTING) CRACKED .024 INCHES BEYOND ALLOWABLE LIMITS.  REPLACED THE REAR SPAR CHORD SEGMENT FROM THE SIDE OF THE FUSELAGE BODY TO REAR SPAR STA 285.  NOTE:  PLEASE REMOVE PIDR AS THE OPERATOR DESIGNATOR IN ORDER TO IDENTIFY THE OPERATOR AS A GENERAL AVIATION OPERATOR.                                                                                                                                                                                                                                                                                                                                                                    2L72 4F    RTA16WE                        
20060918000092006091800009NM  2006       9          18         PIDR2006018      120060814G5711                SPAR                                    BOEING737   737330      13844BJNM                                                               BS 224          CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05241DL                       23833                                   TWO FASTENER HOLES IN THE RIGHT REAR SPAR AT STA 224.14 (AT THE LANDING GEAR BEAM O/B ATTACH FITTING) CRACKED.  REAMED ONE HOLE PER BOEING SB 737-1216R2 AND REAMED SECOND HOLE AND INSTALLED A FREEZE PLUG PER BOEING MESSAGE 1-210954789-9 WITH FAA APPROVED 8100-9 DATED 24 AUG 2006.                                                                                                                                                                                                                                                                                                                                                                                                                                                        2L72 4F    RTA16WE                        
20061018000292006101800029NM  2006       10         18         PIDR2006019      120060928G5315                FLOORBEAM                               BOEING737   7373B7      1384580NM  GE    CFM56 CFM56*      13802NE                              BS 727D         CORRODED        B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05385US                       22958                                   UNDERSIDE OF BS 727D+5 FLOORBEAM IN AFT CARGO BIN IS CORRODED FROM LBL17 TO RBL8.  REPAIRED AREA IAW SRM 53-00-53 FIG. 201.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA16WE   E2GL                 
20061018000282006101800028NM  2006       10         18         PIDR2006020      120060928G5330                SKIN                                    BOEING737   7373B7      1384580NM  GE    CFM56 CFM56*      13802NE                              BS 400 S23R     DENTED          B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05385US                       22958                                   EXISTING DOUBLER ON FUSELAGE AT BS 400 AND S23RT HAS A DENT.  REMOVED EXISTING DOUBLER AND INSTALLED NEW IAW SRM 53-00-01 FIG. 201.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F4  FRTA16WE   E2GL                 
20061018000272006101800027NM  2006       10         18         PIDR2006021      120060928G5330                SKIN                                    BOEING737   7373B7      1384580NM  GE    CFM56 CFM56*      13802NE                              FUSELAGE        WORN            B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05385US                       22958                                   FUSELAGE SKIN WORN UNDER DORSAL FIN.  REPAIRED AREA IAW SB 737-55-1057.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRTA16WE   E2GL                 
20061018000262006101800026NM  2006       10         18         PIDR2006022      120060928G5315                FLOORBEAM                               BOEING737   7373B7      1384580NM  GE    CFM56 CFM56*      13802NE                              BS 312          CORRODED        B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05385US                       22958                                   FLOORBEAM AT BS 312 CORRODED AT NUTPLATE HOLES FROM RBL8 TO RBL32.  REPLACED FLOORBEAM T-CAP IAW SRM 53-10-51.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F4  FRTA16WE   E2GL                 
20061019002312006101900231NM  2006       10         19         PIDR2006023      120060105G5315                FLOORBEAM                               BOEING737   7373B7      1384580NM                                                               BS 986          CORRODED        B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05385US                       22958                                   BS 986.5 FLOORBEAM CORRODED AT A PREVIOUS REPAIR FROM RBL14 TO RBL18.  REPLACED UPPER T CAP OF FLOORBEAM IAW EA NR 53-264.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F    RTA16WE                        
20061013000022006101300002NM  2006       10         13         PIDR2006024      120061010G5315                FLOORBEAM                               BOEING737   7373B7      1384580NM                                                               BS 520          DAMAGED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05385US                       22958                                   VERTICAL WEB OF BS 520 FLOORBEAM DAMAGED AT RBL 36.  REPAIRED DAMAGED AREA IAW EA 53-273.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F    RTA16WE                        
20061013000032006101300003NM  2006       10         13         PIDR2006025      120061011G5330                SKIN                                    BOEING737   7373B7      1384580NM                                                               BS 360-540      DAMAGED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05385US                       22958                                   STR 14 LT SKIN LAP HAS SCRIBE LINE DAMAGE IN SEVERAL PLACES FROM BS 360 TO BS 540.  REPAIRED DAMAGED AREA IAW SB 737-53A1177.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F    RTA16WE                        
20061020000502006102000050NM  2006       10         20         PIDR2006026      120061014G5311                FRAME                                   BOEING737   7373B7      1384580NM                                                               BS 767 S13L     CRACKED         B  PIDRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05385US                       22958                                   CRACK IN BS 767 FRAME AT STR 13 RT.  REPAIRED PER SRM 53-00-07 FIG 201.  NOTE:  PLEASE REMOVE PIDR AS THE OPERATOR DESIGNATOR IN ORDER TO IDENTIFY THE OPERATOR AS A GENERAL AVIATION OPERATOR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F    RTA16WE                        
20061020001262006102000126NM  2006       10         20         PIDR2006027      120061016G5311                FRAME                                   BOEING737   7373B7      1384580NM                                                               BS 867 S13R     CRACKED         B  PIDRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05385US                       22958                                   FOUND CRACK IN BS 867 FRAME AT STR 13RT.  REPAIRED FRAME PER SRM 53-00-07 FIG 201.  PLEASE REMOVE PIDR AS THE OPERATOR DESIGNATOR IN ORDER TO IDENTIFY THE OPERATOR AS A GENERAL AVIATION OPERATOR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F    RTA16WE                        
20061020001272006102000127NM  2006       10         20         PIDR2006028      120061016G5314                KEELBEAM                                BOEING737   7373B7      1384580NM                                                               BS 500D-540     CORRODED        B  PIDRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05385US                       22958                                   CORROSION ON RIGHT KEEL BEAM (STR28RT) FROM BS 500D TO BS 540.  REPAIRED AREA BY SPLICING IN A REPLACEMENT SECTION OF KEEL BEAM PER EA 53-268.  PLEASE REMOVE PIDR AS THE OPERATOR DESIGNATOR IN ORDER TO IDENTIFY THE OPERATOR AS A GENERAL AVIATION OPERATOR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F    RTA16WE                        
20061020001252006102000125NM  2006       10         20         PIDR2006029      120061016G5330                LAP JOINT                               BOEING737   7373B7      1384580NM                                                               BS 360-540      CRACKED         B  PIDRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05385US                       22958                                   CRACK IN LOWER FASTENER ROW OF STR 10LT SKIN LAP AT BS 500D+10 AND VARIOUS LOCATIONS OF SCRIBE LINES AT STR 10LT LAP AREA WERE REPAIRED BY REPLACING THE SKIN LAP PER SB 737-53A1177.  PLEASE REMOVE PIDR AS THE OPERATOR DESIGNATOR IN ORDER TO IDENTIFY THE OPERATOR AS A GENERAL AVIATION OPERATOR.                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA16WE                        
20061020001512006102000151NM  2006       10         20         PIDR2006030      120061011G5330                LAP JOINT                               BOEING737   7373B7      1384580NM                                                               BS 360-540      DAMAGED         B  PIDRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05385US                       22958                                   SEVERAL AREAS OF SCRIBE LINE DAMAGE AT STR 14LT FROM BS 360 TO BS 540.  REPAIRED AREA BY REPLACING THE SKIN LAP PER SB 737-53A1177.  PLEASE REMOVE PIDR AS THE OPERATOR DESIGNATOR IN ORDER TO IDENTIFY THE OPERATOR AS A GENERAL AVIATION OPERATOR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F    RTA16WE                        
20061026001122006102600112NM  2006       10         26         PIDR2006031      120061016G5330                SKIN                                    BOEING737   7373B7      1384580NM                                                               BS 350-360 S25L CORRODED        B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05385US                       22958                                   CORROSION IN FUSELAGE SKIN AT BS 360 AND STR 25 LT.  CORROSION ON STR 25 LT BEYOND ALLOWABLE LIMITS.  SPLICED A NEW PIECE OF STRINGER SECTION AND REMOVED LIGHT SURFACE CORROSION ON FUSELAGE SKIN PER EA 53-270.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F    RTA16WE                        
20061031001522006103100152NM  2006       10         31         PIDR2006032      120061022G5330                SKIN                                    BOEING737   7373B7      1384580NM                                                               BS 727A         CORRODED        B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05385US                       22958                                   CORROSION IN FUSELAGE SKIN IN AREA OF LT KEELBEAM (STR 28LT) AND RT KEELBEAM (STR 28RT)AT BS727A-4.  CUT OUT FUSELAGE SKIN FOR ACCESS TO LT AND RT KEELBEAMS.  REMOVED CORROSION FROM LT AND RT KEELBEAM AREAS WITHIN LIMITS OF SRM 53-60-12 FIG. 101.  REPLACED CORRODED SECTION OF FUSELAGE SKIN IAW EA NR 53-275.                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F    RTA16WE                        
20061031001542006103100154NM  2006       10         31         PIDR2006033      120061016G5311                FRAME                                   BOEING737   737301      1384611NM  GE    CFM56 CFM56*      13802NE                              BS 616          CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05573US                       23560                                   CRACK IN BS 616 FRAME RT SIDE BELOW FLOOR.  REPAIRED DAMAGED AREA IAW SB 737-53-1182.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F4  FRTA16WE   E2GL                 
20061031001532006103100153NM  2006       10         31         PIDR2006034      120061013G5313                STRINGER                                BOEING737   737301      1384611NM  GE    CFM56 CFM56*      13802NE                              BS 312-328      CORRODED        B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05573US                       23560                                   STRINGER 28RT CORRODED BETWEEN BS 312 AND BS 328.  REPLACED STRINGER SECTION IAW SRM 51-40-02.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F4  FRTA16WE   E2GL                 
20061031001552006103100155NM  2006       10         31         PIDR2006035      120061019G5230                BEAM                                    BOEING737   737301      1384611NM  GE    CFM56 CFM56*      13802NE                              CARGO DOOR      CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05573US                       23560                                   LOWER LT AND RT INTERNAL BEAMS CRACKED.  REPAIRED BEAMS SB 737-52A1079.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F4  FRTA16WE   E2GL                 
20061031001712006103100171NM  2006       10         31         PIDR2006036      120061026G5330                SKIN                                    BOEING737   7373B7      1384580NM                                                               BS 328-332      CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05385US                       22958                                   CRACK IN FUSELAGE SKIN AT AFT LOWER CORNER OF FORWARD SERVICE DOOR (R1).  NDT CONFIRMED ADDITIONAL CRACK IN BONDED DOUBLER.  REPAIRED AREA IAW SRM 53-00-01 FIG. 201 REPAIR 32 AND EA NR 53-265.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F    RTA16WE                        
20061031001402006103100140NM  2006       10         31         PIDR2006037      120061023G5311                FRAME                                   BOEING737   7373B7      1384580NM                                                               BS 663 S2-3R    CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05385US                       22958                                   CRACKS IN BS663.75 FRAME AT STR 2RT AND STR 3RT.  REPAIRED FRAME IAW SRM 53-00-07.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F    RTA16WE                        
20061106000812006110600081NM  2006       11         6          PIDR2006038      120061027G5743                FITTING                                 BOEING737   737301      1384611NM  GE    CFM56 CFM56*      13802NE                              LT MLG          CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05573US                       23560                                   LT MLG FITTINGS CRACKED AT THE NR 2 HOLE.  REPLACED FITTING IAW SB 737-57-1216.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F4  FRTA16WE   E2GL                 
20061106000822006110600082NM  2006       11         6          PIDR2006039      120061101G5753                SKIN                                    BOEING737   737301      1384611NM  GE    CFM56 CFM56*      13802NE                              LT FORE FLAP    DELAMINATED     B  PIDRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05573US                       23560                                   DELAMINATION AT THE IB END OF THE LT OB FORE FLAP.  REPAIRED DAMAGED AREA IAW SRM 51-70-10.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F4  FRTA16WE   E2GL                 
20061106000802006110600080NM  2006       11         6          PIDR2006040      120061031G5752                TAB                                     BOEING737   7373B7      1384580NM  GE    CFM56 CFM56*      13802NE                              RT AILERON      SEPARATED       B  PIDRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05385US                       22958                                   TRAILING EDGE OF THE RT AILERON TAB IS SEPARATED.  REPAIRED MINOR DAMAGE PER SRM 51-70-16. BALANCED TAB, NO WEIGHT CHANGE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F4  FRTA16WE   E2GL                 
20061115003172006111500317NM  2006       11         15         PIDR2006041      120061107G5311                FRAME                                   BOEING737   737301      1384611NM  GE    CFM56 CFM56*      13802NE                              BS 440          CRACKED         B  PIDRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05573US                       23560                                   FORWARD FRAME OF THE FORWARD CARGO DOOR CUTOUT (BS 440 FRAME) CRACKED AT LOWER FORWARD STOP FITTING.  REPAIRED CRACK PER INSTRUCTIONS FROM MFG WITH FAA APPROVED 8100-9 DATED NOV.6, 2006.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F4  FRTA16WE   E2GL                 
20061115003192006111500319NM  2006       11         15         PIDR2006042      120061031G5330                BEAR STRAP                              BOEING737   737301      1384611NM  GE    CFM56 CFM56*      13802NE                              FUSELAGE        CRACKED         B  PIDRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05573US                       23560                                   CRACK INDICATION IN FASTENER HOLE JUST FORWARD AND BELOW THE L1 DOOR UPPER HINGE CUTOUT IN THE BEAR STRAP (SECOND LAYER) CONFIRMED BY HFEC.  REPAIRED IAW MFG INSTRUCTIONS WITH FAA APPROVED 8100-9 DATED NOV 3, 2006.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F4  FRTA16WE   E2GL                 
20061115002272006111500227NM  2006       11         15         PIDR2006043      120061026G534265538344        FITTING                                 BOEING737   7373B7      1384580NM                                                               DRAG ANGLE      CORRODED        B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05385US                       22958                                   CORROSION ON THE FORWARD FACE AND INSIDE DIAMETER OF THE RT FORWARD DRAG ANGLE FITTING AT THE VERTICAL STABILIZER AFT RT ATTACH FITTING.  REPLACED FITTING IAW SRM 51-40-02, 51-40-03, AND DRAWING NR 65-53744.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F    RTA16WE                        
20061115002302006111500230NM  2006       11         15         PIDR2006044      120061103G5330                SKIN                                    BOEING737   7373B7      1384580NM                                                               FUSELAGE        DAMAGED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05385US                       22958                                   FASTENER HOLES JUST FORWARD AND ABOVE THE RIGHT FWD DOOR UPPER HINGE CUTOUT AND JUST FORWARD OF THE LOWER HINGE CUTOUT ARE CRACKED.  REPAIRED SKIN AND BEAR STRAP IAW MESSAGES 1-232472835 WITH FAA DER APPROVED 8100-9 DATED NOV. 3, 2006.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F    RTA16WE                        
20061115002282006111500228NM  2006       11         15         PIDR2006045      120061103G5310                STRUCTURE                               BOEING737   7373B7      1384580NM                                                               FUSELAGE        CRACKED         B  PIDRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05385US                       22958                                   FASTENER HOLES CRACKED AT THE UPPER HINGE CUTOUT AND LOWER HINGE CUTOUT OF THE LT FORWARD ENTRY DOOR. REPAIRED AREA IAW MESSAGE 1-232472835 WITH FAA DER APPROVED 8100-9 DATED NOV.3, 2006.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F    RTA16WE                        
20061205000072006120500007NM  2006       12         5          PIDR2006046      120061115G5754                SLAT                                    BOEING737   7373B7      1384580NM                                                               LT WING         DAMAGED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05385US                       22958                                   LT WING LEADING EDGE AT THE OB END OF THE NR3 SLAT DAMAGED.  REPAIRED DAMAGE PER SRM 51-70-11, 51-70-14, AND 51-70-16.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA16WE                        
20061117001712006111700171NM  2006       11         17         PIDR2006047      120061115G5520                HINGE                                   BOEING737   7373B7      1384580NM                                                               RT ELEVATOR     DAMAGED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05385US                       22958                                   RT ELEVATOR LOWER SIDE AT NR 5 HINGE HAS DAMAGE.  REPAIRED IAW SRM 51-70-17 AND MFG MESSAGE NR 1-247071893 WITH FAA DOA APPROVAL FORM 8100-9.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F    RTA16WE                        
20060724000312006072400031GL  2006       7          24         PNC2006001       120060718G3244269K431         TIRE                                    BOMBDRBD700 BD7001A10   1390006GL                                                               LANDING GEAR    BULGED          D      K   NONE                                                                                            O  OTHER                                                                         LDLANDING        1                      EA03387PC78                     20087                                   SIDE WALL BULGED 4 INCHES BY 4 INCHES BY APPROX 3 INCHES HIGH.  ISSUE ADDRESSED BY ADVISORY WIRE AW300-32-0040.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                 2L72 4F    RTT00003NY                     
20060816003052006081600305GL  2006       8          16         PNC2006004       120060814G3244269K431         TIRE                                    BOMBDRBD100 BD1001A10   1390044GL                                                               ZONE 700        BULGED          C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA03387PC91                     20087                                   BULGE IN TIRE ON SIDEWALL THAT EXTENDS ONTO THE TREAD.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTT00005NY                     
20060724000842006072400084GL  2006       7          24         PNC20062         120060721G3244269K431         TIRE                                    BOMBDRBD100 BD1001A10   1390044GL                                                               LANDING GEAR    BULGED          C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA03353PC137                    20053                                   BULGE ON SIDEWALL OF TIRE THAT EXTENDS INTO THE TREAD.  BULGE SIZE 2.5 INCHES X 2.5 INCHES X .7INCH HIGH.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F    RTT00005NY                     
20060724000792006072400079GL  2006       7          24         PNC20063         120060721G3244269K431         TIRE                                    BOMBDRBD100 BD1001A10   1390044GL                                                               LANDING GEAR    SEPARATED       C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA03353PC94                     20053                                   TIRE SIDEWALL SEPERTED AT SEVERAL LOCATIONS ABOUT ONE INCH ABOVE BEAD SEAT,NEAR MOLDING MARK. ABOUT A ONE INCH LONG VOID.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F    RTT00005NY                     
20060816003062006081600306GL  2006       8          16         PNC20064         120060814G3244269K431         TIRE                                    BOMBDRBD100 BD1001A10   1390044GL                                                                               BULGED          C      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      EA03387PC91                     20087                                   BULGE IN TIRE ON SIDEWALL THAT EXTENDS ONTO THE TREAD.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTT00005NY                     
20060724000342006072400034CE  2006       7          24         PT196042         120060615G61239638003013      JAM-NUT                                 BEECH 58    58          1152740CE  CONT  O550  IO550C           SO                              PROP GOVERNOR   LOOSE           D      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL03376W 550                    TH1970      684427                      RT PROPELLER RPM DECREASES TOWARD FEATHER BEFORE PROP CONTROL IS BROUGHT BACK INTO FEATHER DETENT.  FOUND JAM NUT ON FEATHER SPEED ADJUSTMENT SCREW HAD WORKED LOOSE AND THE ADJUSTMENT SCREW WAS BACKING OUT.  THE DESIGN OF THESE NUTS HAS BEEN CHANGED IN THE LAST FEW YEARS, THE EARLY TYPE DID NOT SEEM TO LOOSEN.  IF THE ADJUSTMENT SCREW HAD CONTINUED TO BACK OUT, THE ENGINE COULD HAVE EXPERIENCED AN UNCOMMANDED FEATHER WITH LITTLE OR NO WARNING.  SUGGEST CHECKING TORQUE OF JAM NUT AT EACH INSPECTION AND APPLICATION OF TORQUE PUTTY UNTIL BETTER RETENTION SYSTEM IS DEVELOPED.  (K)                                                                                                                                         1L72 3O3  O  3A16    E3SO                 
20061219001552006121900155    2006       12         19         QKPR06001        120060912G493038828406        FCU             HONEYWELL   GTCP36150RR                                                                                                 ENGINE          LEAKING         B  QKPRK   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      SO05                                                                    FUEL PRESSURE IN THE DIFFERENTIAL PRESSURE VALVE IS CAUSING SEVERE PITTING INSIDE THE FCU HOUSING.  THIS PITTING EVENTUALLY BECOMES A PIN HOLE IN THE HOUSING.  THIS PIN HOLE ALLOWS A STREAM OF FUEL, AT IDLE AND WHEN PRESSURE IS APPLIED, TO EXIT THE FCU.  POTENTIALLY, IF THIS PROBLEM IS NOT CORRECTED IT COULD CREATE A FIRE HAZZARD.                                                                                                                                                                                                                                                                                                                                                                                                                                              
20061219001082006121900108    2006       12         19         QKPR06002        120060912G493038828406        FCU             HONEYWELL   GTCP36150RR                                                                                                 ENGINE          LEAKING         B  QKPRK   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      SO05                                                                    FUEL PRESSURE IN THE DIFFERENTIAL PRESSURE VALVE IS CAUSING SEVERE PITTING INSIDE THE FCU HOUSING.  THIS PITTING EVENTUALLY BECOMES A PIN HOLE IN THE HOUSING.  THIS PIN HOLE ALLOWS A STREAM OF FUEL, AT IDLE AND WHEN PRESSURE IS APPLIED, TO EXIT THE FCU.  POTENTIALLY, IF THIS PROBLEM IS NOT CORRECTED IT COULD CREATE A FIRE HAZZARD.                                                                                                                                                                                                                                                                                                                                                                                                                                              
20061219001562006121900156    2006       12         19         QKPR06003        120060629G493038828406        FCU             HONEYWELL   GTCP36150RR                                                                                                 ENGINE          LEAKING         B  QKPRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05                P254                                                FUEL PRESSURE IN THE DIFFERENTIAL PRESSURE VALVE IS CAUSING SEVERE PITTING INSIDE THE FCU HOUSING.  THIS PITTING EVENTUALLY BECOMES A PIN HOLE IN THE HOUSING.  THIS PIN HOLE ALLOWS A STREAM OF FUEL, AT IDLE AND WHEN PRESSURE IS APPLIED, TO EXIT THE FCU.  POTENTIALLY, IF THIS PROBLEM IS NOT CORRECTED, IT COULD CREATE A FIRE HAZZARD.    ORIGINAL DIFFICULTY DATE 6/29/01.                                                                                                                                                                                                                                                                                                                                                                                                        
20070108002822007010800282GL  2007       1          8          QKPR06007        120060815G493038828406        FUEL CONTROL    HONEYWELL   GTCT36150RR DOUG  A4D   A4D                GL                                                               APU             LEAKING         B  QKPRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO05                                                                    FUEL PRESSURE IN THE DIFFERENTIAL PRESSURE VALVE IS CAUSING SEVERE PITTING INSIDE THE FCU HOUSING.  THIS PITTING EVENTUALLY BECOMES A PIN HOLE IN THE HOUSING. THIS PIN HOLE ALLOWS A STREAM OF FUEL, AT IDLE AND WHEN PRESSURE IS APPLIED, TO EXIT THE FCU. POTENTIALLY, IF THIS PROBLEM IS NOT CORRECTED IT COULD CREATE A FIRE HAZARD.  * REMOVE AIRCRAFT INFORMATION. REPORT ORIGINALLY SUBMITTED ON 8/15/01 UNDER R/S NR PIDR318B.                                                                                                                                                                                                                                                                                                         2L71 4R    RTA1GL                         
20070108002882007010800288GL  2007       1          8          QKPR06009        120060918G493038828406        FUEL CONTROL    HONEYWELL   GTCT36150RR DOUG  A4D   A4D                GL                                                               APU             LEAKING         B  QKPRO   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      SO05                                                                    FUEL PRESSURE IN THE DIFFERENTIAL PRESSURE VALVE IS CAUSING SEVERE PITTING INSIDE THE FCU HOUSING.  THIS PITTING EVENTUALLY BECOMES A PIN HOLE IN THE HOUSING. THIS PIN HOLE ALLOWS A STREAM OF FUEL, AT IDLE AND WHEN PRESSURE IS APPLIED, TO EXIT THE FCU. POTENTIALLY, IF THIS PROBLEM IS NOT CORRECTED IT COULD CREATE A FIRE HAZARD.  * REMOVE AIRCRAFT INFORMATION.                                                                                                                                                                                                                                                                                                                                                                       2L71 4R    RTA1GL                         
20060224001982006022400198NE  2006       2          24         R018276          320060120G6114C459            PLATE           HARTZL                                                                                      HARTZLHCE4N HCE4N3      NE  PROPELLER HUB   GOUGED          B      K   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      GL05SJ3R            HH2369                              HH2369          C-459 PRELOAD PLATE.  THREE PRELOAD PLATES FOUND TO BE DAMAGED BEYOND REPAIRABLE LIMITS.  GOUGE IS LOCATED OPPOSITE OF THE WINDOW AND IS APPROXIMATELY 0.030 WIDE BY 1 INCH LONG BY 0.020 DEEP.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              5  CP10NE    
20060224001952006022400195NE  2006       2          24         R018683          320060120G6114                PLATE           HARTZL                                                                                      HARTZLHCE4N HCE4N3      NE  PROPELLER HUB   GOUGED          B      K   NONE                                                                                            O  OTHER                                                                         NRNOT REPORTED   1                      GL05SJ3R            HH2422                              HH2422          C-459 PRELOAD PLATE.  GOUGE IS APPROXIMATELY 1.120 INCH LONG BY 0.050 INCH WIDE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             5  CP10NE    
20060201001262006020100126GL  2006       2          1          R018909          320060128G6110                O-RING          HARTZL      HCC2YR4CF                                                                       HARTZLHCC2Y HCC2YR4     GL  PROPELLER BLADESWRONG PART      B      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL05SJ3R            DN5325B                             DN5325B         PROP LEAKING GREASE FROM BLADES. INSPECTION REVEALED INCORRECT BLADE SEALS INSTALLED. SRM 113B REQUIRES ITEM 540, B-3883-4339 QUAD RING WITH NO ALTERNATE. SEALS REMOVED FROM PROPELLER ARE O-RINGS.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         5  CP920     
20060322001922006032200192GL  2006       3          22         R019142          320060222G6110D32517          HUB             HARTZL                  CESSNA340   340CESSNA   2076404CE  CONT  O520  TSIO520NB   17040SO  HARTZLHCC3Y PHCC3YF2    GL  PROPELLER ASSY  CRACKED         B  SJ3RK   NONE                                                                                            K  FLUID LOSS                                                                    ININSP/MAINT     1                      GL05SJ3R            EB2069                              EB2069          CUSTOMER WAS INVESTIGATING AN ABNORMAL GREASE LEAK ON THE RIGHT HAND PROPELLER.  REMOVED THE SPINNER, DISCOVERED THAT THE ENGINE-SIDE HUB HALF WAS VISIBLY CRACKED.  CRACKS ARE LOCATED ON THE PROPELLER MOUNTING FLANGE HUB HALF, LEAD EDGE SIDE OF BLADE SOCKETS NUMBER 1 AND 2.  CRACKS RUN FROM HUB PARTING SURFACE TO MOUNTING FLANGE.                                                                                                                                                                                                                                                                                                                                                                                                     1L72 3O3  O  3A25    E8CE    5  CP25EA    
20060321000482006032100048GL  2006       3          21         R019184          320060306G6110B4776           BUSHING         HARTZL      HCC3YR1A    PITTS S2B   S2B         2210006SO  LYC   O540  AEIO540D4A5 41532EA  HARTZLHCC3Y HCC3YR      GL  PROPELLER ASSY  LOOSE           B  SJ3RO   OTHER                                                                                           KJ FLUID LOSS                WARNING INDICATION                                  NRNOT REPORTED   1                      GL05SJ3R            EL270B                              EL270B          CUSTOMER REMOVED PROP DUE TO OIL LEAKING FROM BLADE.  DISASSEMBLY OF THE PROPELLER REVEALED A LOOSE PITCH CHANGE ROD BORE BUSHING CAUSING THE OIL LEAK.  THE PC ROD BUSHING WAS FOUND WEDGED BETWEEN THE FORK AND HUB.  CENTRAL WEB AREA OF HUB WAS FULL OF OIL.  THE PC ROD BORE BUSHING HAD BEEN INSTALLED AT OVERHAUL IN ACCORDANCE WITH HARTZELL MANUAL 202A VOLUME 3 REVISION 28.                                                                                                                                                                                                                                                                                                                                                          1Q71 3O3  ONCA8SO    1E4     5  CP25EA    
20060321001182006032100118NE  2006       3          21         R019280          320060303G6110D7745           BEARING RACE    HARTZL      HCE4A3I     BEECH 1900  1900D       1154162CE  PWA   PT6   PT6A67D          NE  HARTZLHCE4A HCE4A3I     NE  PROPELLER       BROKEN          B  SJ3RO   OTHER                                                                                           E  VIBRATION/BUFFET                                                              NRNOT REPORTED   1                      GL05SJ3R 2134       KX201                               KX201           CUSTOMER REMOVED PROPELLER DUE TO LOOSE BLADE IAW HARTZELL SERVICE BULLETIN HC-SB-61-283.  ONE D-7745 BLADE SIDE BEARING INSTALLED ON BLADE SERIAL NUMBER 2828 WAS FOUND CRACKED CIRCUMFERENTIALLY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4T4  TRTA24CE   E26NE   5  CP10NE    
20060530001672006053000167SO  2006       5          30         R019692          120060519G6120C6512           ROD             HARTZL      PHCG3YF1E   PIPER PA46  PA46310P    7104605SO  CONT  O520  TSIO520BE   17040SO  HARTZLHCC2Y BHCC2Y*     GL  ENGINE          WORN            B  SJ3RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05SJ3R 1338       HP900B                              HP900B          THE AREA OF THE PITCH CHANGE ROD THAT IS GUIDED THROUGH THE ENGINE SIDE HUB HALF BORE HAS WORN THROUGH THE CHROME PLATING BEFORE FIRST OVERHAUL.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L71 3O3  ORTA25SO   E8CE    5  CP920     
20060914000722006091400072NE  2006       9          14         R020646          320060824G61101006411         PLATE                       HCE4A3J     BEECH 1900  1900D       1154162CE  PWA   PT6   PT6*        52043EA  HARTZLHCE4A HCE4A3A     NE  PROPELLER       MISMARKED       B  SJ3RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05     522        HJ1190      UE370                   HJ1190          PRELOAD PLATES ARE MARKED WITH PN 100641 BUT CONFIGURED AS PN 100641-1. LOGBOOK INDICATES PROP WAS REMOVED ON 5/17/05 FROM AIRCRAFT D2-EVN, S/N UE-370 RT POSITION DUE TO DEEP GOUGE OVER ACCEPTABLE LIMITS.  PROP WAS OVERHAULED ON 7/14/05 WITH 824.0 TSN.  PRELOADS MAY HAVE BEEN INSTALLED AT THIS TIME IAW S/B HC-SB-61-278.  I DO NOT KNOW IF THE BEARINGS WERE REMOVED TO MAKE P/N 100641-1 OR THE PART WAS INCORRECTLY MARKED AT HPI.                                                                                                                                                                                                                                                                                                   2L72 4T3  TRTA24CE   E2NE    5  CP10NE    
20070104000712007010400071CE  2007       1          4          RDA113006        120061130G2437VA100           AMMETER                                 CESSNA175   175         2072502CE                                                                               FAILED          G      O   OTHER                                                                                           O  OTHER                                                                         NRNOT REPORTED   1                      GL239456B18                     55256                                   AEROSPACE LOGIC VA-100 DIGITAL VOLT/AMMETER AMP FUNCTION FAILED.  AMP READING VARIES FROM -12 TO -18.5 AMPS, THIS INDICATION IS PRESENT WITH NO LOAD ON SYSTEM OR WITH ENGINE OPERATING AND GENERATOR OPERATING NORMALLY.  VOLT FUNCTION OPERATES NORMALLY AND VOLTAGE READING IS NORMAL.  CONSULTED WITH MANUFACTURER AND TROUBLESHOT IAW THEIR PROCEDURE TO VERIFY THAT GAUGE HAS MALFUNCTIONED.  A REVIEW OF THE MANUFACTURER'S ON-LINE FORUM HAS REPORTS OF SIMILAR FAILURES OF THE VA-100.                                                                                                                                                                                                                                                 1H71 3O    NT3A17                         
20060228000202006022800020WP  2006       2          28         ROBSUL0106       120060203G5302C0231           STRUCTURE                               ROBSINR44   R44RAVENII  7640122WP                                                               TAILBOOM        DENTED          Z      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW99105GK185                    10527                                   DURING 100 HOUR/ANNUAL INSPECTION A DENT WAS FOUND ON THE TAILBOOM CAUSED BY M/R BLADE CONTACT WITH BOOM. DUE TO SUSPECTED STATIC CONTACT DURING HIGH WIND CAUSING ROTOR SYSTEM TO TEETER RAPIDLY AND CONTACT BOOM.  ADDITIONAL DAMAGE FOUND WITH BENDING OF PITCH LINK ROD ENDS AND CONTACT WITH HUB OF THE RUBBER BOOTS OF THE SPINDLE PITCH HORNS.  THIUS DAMAGE CONSISTENT WITH BLADE RISING DUE TO HIGH WIND.                                                                                                                                                                                                                                                                                                                              1G71 3O      H11NM                        
20060511002542006051100254SO  2006       5          11         RX8R2006001      120060410G32305777402         HYDRAULIC LINE                          PIPER PA42  PA42720     7104212SO  PWA   PT6   PT6A61      52043EA  HARTZLHCB3T HCB3TN3     GL  LG RETRACT SYS  DAMAGED         B  RX8RA   UNSCHED LANDING                                                                                 K  FLUID LOSS                                                                    CLCLIMB          1                      SO159085U5679                   425501034   PCE99076    BUA26367        AFTER TAKEOFF THE LANDING GEAR HANDLE WAS MOVED TO THE UP POSITION THE LANDING GEAR CAME UP BUT THE GEAR DOORS DID NOT CLOSE. THE LANDING GEAR HANDLE WAS PUT IN THE DOWN POSITION BUT THE LANDING GEAR DID NOT LOCK DOWN. THE EMERGENCY HAND PUMP WAS USED TO MAKE THE LANDING GEAR LOCK IN THE DOWN POSITION. THE AIRCRAFT WAS LANDED WITHOUT INCIDENT. DISCOVERED  HYDRAULIC LINE FROM HYDRAULIC FILTER WAS RUBBING ON NUT PLATE AND HAD WORN A HOLE IN IT. RIGHT WING TO NACELLE AREA WAS INSPECTED AND THE SAME HYDRAULIC LINE WAS FOUND RUBBING IN THE SAME AREA BUT HAD NOT WORN THROUGH. RECOMMEND INSPECTING THIS AREA ON ALL PA42-720 AIRCRAFT. AREA LOCATED BEHIND SMALL (FOUR INCH) PANEL JUST INBOARD OF THE ENGINE NACELLE ON LE. 1L72 4T4  T  A23SO   E4EA    6  CP15EA    
20060620000122006062000012EU  2006       6          20         RX8R2006002      120060607G7603L810BQ54        SOLENOID                                SNIAS 350   AS350B3     8680954EU  TMECA ARRIELARRIEL2B         NE                              THROTTLE SYS    DEFECTIVE       B  RX8RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO15578AE                       3716        22381                       TWIST GRIP SOLENOID DOES NOT STAY IN THE MANUAL MODE POSITION (RETRACTED) WHEN MANUAL MODE IS SELECTED.  AFTER APPROXIMATELY 5 MINUTES SOLENOID WILL GRADUALLY EXTEND, LOCKING THE TWIST GRIP IN THE AUTO POSITION AS THE SOLENOID HEATS UP FROM USE.  THIS COULD CREATE A BIG PROBLEM IN AN EMERGENCY SITUATION WHERE THE PILOT SELECTS MANUAL MODE FOR CONTROL OF TWIST GRIP FOR POWER AND WOULD NOT HAVE IT (AFTER APPROX 5 MINUTES) DUE TO SOLENOID LOCKING THE TWIST GRIP.  NOTE: THIS PART WAS JUST INSTALLED, NEW.                                                                                                                                                                                                                       1G71 3U3  U  H9EU    E00054EN             
20060814001452006081400145SO  2006       8          14         RX8R2006003      120060807G52804579411AND12    STRUCTURE                               PIPER PA42  PA42720     7104212SO  PWA   PT6   PT6A61      52043EA  HARTZLHCB3T HCB3TN3     GL  NLG DOOR        CRACKED         B  RX8RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO159085U5726                   425501034   PCE99076    BUA26367        FOUND CRACK IN LT NOSE LANDING GEAR DOOR ON RADIUS OF FRONT STIFFENER SECTION. ALSO FOUND CRACK IN RT NOSE LANDING GEAR DOOR AT FORWARD HINGE ATTACH POINT. HAVE PREVIOUSLY FOUND CRACKS IN THE NOSE LANDING GEAR DOORS ON 4 OTHER PA-42'S. THE CRACKS ARE USUALLY IN THE DOOR HINGE ATTACH AREA. WE BELIEVE THE CRACKS ARE BEING CAUSED BY IN FLIGHT TURBULENCE, CAUSING THE DOORS TO VIBRATE IN FLIGHT.                                                                                                                                                                                                                                                                                                                                       1L72 4T4  T  A23SO   E4EA    6  CP15EA    
20060201000752006020100075NE  2006       2          1          SJ3R018954       320060128G6114D7745           BEARING         HARTZL      HCE4A3I                                                                         HARTZLHCE4A HCE4A3I     NE  PROPELLER HUB   BROKEN          B  SJ3RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05                HJ1533                              HJ1533          OPERATOR FAILED PROPELLER FOR BLADE END PLAY IAW SB HC-SB-61-283 AND SERVICE LETTER HC-SL-61-215.  AFTER DISASSEMBLY, INSPECTION REVEALED ONE BROKEN D-7745 BLADE THRUST BEARING INSTALLED ON BLADE S/N 288MA LOCATED IN HUB SOCKET NR 3.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    5  CP10NE    
20060825000482006082500048GL  2006       8          25         SJ3R020511       320060809G6114D32511R         HUB             HARTZL                  INLANDS300  S300        4551002CE  LYC   O540  AEIO540*         EA  HARTZLHCC3Y HCC3YR      GL  PROPELLER       DAMAGED         B  SJ3RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05     790        HTA1                                HTA1            PROPELLER MOUNTING FLANGE HAS EXCESSIVE FRETTING DAMAGE.  HUB IS SCRAP.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         1H71 3R3  O  ATC259  1E4     5  CP25EA    
20070125000912007012500091NE  2007       1          25         SJ3R021444       320061118G6110D7745           BEARING         HARTZL      HCE4A3J     BEECH 1900  1900D       1154162CE  PWA   PT6   PT6*        52043EA  HARTZLHCE4A HCE4A3A     NE  PROPELLER BLADE BROKEN          B  SJ3RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL05                HJ1797                              HJ1797          BLADE POSITION 4, S/N 1091 THRUST BEARING BROKEN.  DAMAGE TO PROPELLER HUB BLADE SOCKET NR 4  IS BEYOND REPAIRABLE LIMITS.  MFG SB 287 HAS NOT BEEN PERFORMED ON THIS PROPELLER.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4T3  TRTA24CE   E2NE    5  CP10NE    
20060512000702006051200070NM  2006       5          12         SROM200600001    120060329G5313652072623       LONGERON                                BOEING737   737205      1384456NM                                                               FUSELAGE        CRACKED         C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03733PA364551951              23466                                   DURING HEAVY MAINTENANCE INSPECTION FOUND CRACKS IN UPPER FLANGE RADIUS OF LONGERON/WEB P/N 65-20726-23 AT STA 455 AND 470, STR 26R.   REMOVED WEB BETWEEN STA 440 - 493, FABRICATED REPLACEMENT WEB WITH 7075-T6 .063, IN LIEU OF ORIGINAL .056, AND INSTALLED IAW SRM AND MFG DRAWING NO 65-20726 AS SPECIFIED IN 8110-3 APPROVED DRAWING 5330-236-ERA, REV ORIGINAL, DATED 03-23-2006 AND MATERIAL SUBSTITUTION REPORT NO 5330236-ER, REV. ORIGINAL, DATED 03-23-2006.                                                                                                                                                                                                                                                                       2L72 4F    RTA16WE                        
20060512000712006051200071NM  2006       5          12         SROM200600002    120060330G783065MK784132      THRUST REVERSER                         BOEING737   737205      1384456NM                                                               ENGINE          CRACKED         C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03733PA                       23466                                   DURING MAINTENANCE INSPECTION FOUND CRACK IN NR 2 LOWER THRUST REVERSER DOOR P/N 65MK78413-2 ALONG IB BUMPER.  REMOVED BUMPER, STOP DRILLED CRACK, FABRICATE/INSTALL DOUBLER AND TRIPLER.  FABRICATE AND INSTALL NEW CAP TO COMPENSATE FOR DOUBLER AND TRIPLER.  ALL WORK ACCOMPLISHED IAW 8110-3 APPROVED DRAWING NR 7830233-1, REV ORIGINAL, DATED 03-20-2006 AND MATERIAL SUBSTITUTION REPORT NR 7830233-ER, REV ORIGINAL, DATED 03-20-2006.                                                                                                                                                                                                                                                                                                 2L72 4F    RTA16WE                        
20060512000722006051200072NM  2006       5          12         SROM200600003    120060316G5753657194041       FLAP                                    BOEING737   737205      1384456NM  PWA   JT8   JT8D17      52049NE                              LT WING         DENTED          C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03733PA     1951              23466                                   DURING HEAVY MAINTENANCE VISIT FOUND DENT ON UPPER SURFACE OF LT IB MIDFLAP.  REPAIRED FLAP BY INSTALLING INTERNAL DOUBLER AND FLUSH PART IN IAW SRM 57-50-4, FIG. 4 PG. 8 AND 9.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F4  FRTA16WE   E2EA                 
20060511002042006051100204NM  2006       5          11         SROM200600004    120060403G5730                SKIN                                    BOEING737   737205      1384456NM                                                               ZONE 600        CRACKED         C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03736BP     882               23465                                   RT WING LEADING EDGE CRACKED AT NR 5 SLAT UPSTOP CUTOUT JUST OB OF THE ACTUATOR.  REPAIRED BY INSTALLING INTERNAL STAINLESS DOUBLER IAW DER APPROVED 8110, REPORT NR SCS-5740-001SR.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F    RTA16WE                        
20060530001552006053000155NM  2006       5          30         SROM200600005    120060503G5313                STRINGER                                BOEING737   737201      1384454NM                                                               FUSELAGE        CORRODED        C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03245US     1210              22751                                   DURING HEAVY MAINTENANCE INSPECTION FOUND CORROSION AT STR 28 LT, STA 1000 TO 1006.  CORROSION FOUND TO BE BEYOND LIMITS.  STRINGER REPLACED I.A.W. B737 SRM 53-10-2 AND 51-10-1 PG. 9 PARA 7.  STRINGER REPLACED STA 986 - 1016 PLUS/MINUS 28".  ORIGINAL SPLICE REUSED.  SPLICE PIECE CLEANED AND PAINTED.  LEVEL 1 CPCP ISOLATED TO LAV LEAK AND NOT EXPERIENCED ACROSS THE FLEET.                                                                                                                                                                                                                                                                                                                                                           2L72 4F      A16WE                        
20060530001512006053000151NM  2006       5          30         SROM200600006    120060510G5330                SKIN                                    BOEING737   737201      1384454NM                                                               FUSELAGE        CRACKED         C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03245US     1210              22751                                   DURING HEAVY MAINTENANCE INSPECTION FOUND SKIN CRACK UNDER RT WING TO BODY FAIRING AT STA 727B, STR 19R.  REMOVED EXSISTING ADJACENT PATCH AT STA 727A, STR 18R.  INSTALLED PATCH, INCORPORATING OLD REPAIR AND NEW DAMAGE IAW B737 SRM FIG. 48, 55-30-3 AND BOEING ENGINEERING 1-185385517-1.                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F      A16WE                        
20060530001532006053000153NM  2006       5          30         SROM200600008    120060516G321065461406SPL     BOLT            BOEING      B737200     BOEING737   737201      1384454NM                                                               LT MLG          CRACKED         C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03245US295719248  XC89752     22751                                   DURING INSPECTION REQUIREMENTS OF AD2005-20-39, SB737-32A1367 FOUND LT MLG TEE BOLT, P/N 65-46140-6SPL, S/N XZ865 CRACKED AT RADIUS OF LARGEST BEARING SURFACE CIRCUMFERENCE.  UNIT HAD TOTAL HOURS OF 29571, TOTAL CYCLES 22830.  LAST OVERHAULED 1998 WITH ACCUMULATION OF 9248 HOURS AND 5265 CYCLES SINCE OVERHAUL.  CRACK WAS AROUND 80% OF CIRCUMFERENCE.  REPLACED WITH SERVICABLE UNIT.                                                                                                                                                                                                                                                                                                                                                 2L72 4F      A16WE                        
20060530001542006053000154NM  2006       5          30         SROM200600009    120060517G5330                SKIN                                    BOEING737   737201      1384454NM                                                               FUSELAGE        DENTED          C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03245US535811210              22751                                   DURING HEAVY CHECK INSPECTION DISCOVERED 9 CREASE/DENTS ON EXTERIOR SKIN AT STA 305 - 372, STR 23R - STR 24R.  REPAIRED EXTERIOR SKIN IAW B 737 SRM FIGURE 48, DETAIL XXIX AND XIX.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             2L72 4F      A16WE                        
20060613003802006061300380NE  2006       6          13         SROM200600010    220060523G7250648031          CASE                                    BOEING737   737201      1384454NM  PWA   JT8   JT8D15      52051NE                              NR 2 ENGINE     CRACKED         I  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03245US     1210              22751       696531                      DURING HEAVY MAINTENANCE INSPECTION FOUND CRACKED OUT SECTION IN REAR EXHAUST CASE OF NR 2 ENGINE.  REPLACED WITH OVERHAULED UNIT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                              2L72 4F4  F  A16WE   E2EA                 
20060530000842006053000084NM  2006       5          30         SROM200600011    120060510G575365682979        CARRIAGE                                BOEING737   737201      1384454NM                                                               ZONE 500        CORRODED        C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03245US     15552             22751                                   DURING HEAVY MAINTENANCE CHECK WHILE PERFORMING A 10 YEAR CPCP INSPECTION REQUIREMENTS OF THE TRAILING EDGE FLAP CARRIAGES FOUND LEVEL 2 CORROSION ON NR 3 CARRIAGE OB CARRIAGE HALF.  REPLACED WITH NEW HALF V/S REPAIR FOR COMPANY CONVENIENCE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F      A16WE                        
20060530001192006053000119NM  2006       5          30         SROM200600012    120060510G5753656829710       CARRIAGE                                BOEING737   737201      1384454NM                                                               WING            CORRODED        C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03245US     15552             22751                                   DURING HEAVY MAINTENANCE CHECK WHILE PERFORMING  CPCP 10 YEAR REQUIREMENTS TO THE TRAILING EDGE FLAP CARRIAGES FOUND THE NR 3 TRAILING EDGE FLAP CARRIAGE IB CARRIAGE HALF TO HAVE LEVEL 2 CORROSION.  REMOVED AND REPLACED WITH NEW UNIT V/S REPAIR FOR COMPANY CONVENIENCE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F      A16WE                        
20060530001212006053000121NM  2006       5          30         SROM200600013    120060524G5753655224618       CARRIAGE                                BOEING737   737201      1384454NM                                                               TE FLAP         CORRODED        C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03245US     15552             22751                                   DURING HEAVY MAINTENANCE CHECK WHILE PERFORMING 10 YEAR CPCP REQUIREMENTS TO TRAILING EDGE FLAP CARRIAGES FOUND NR 5 CARRIAGE, INBD CARRIAGE HALF CORRODED.  LEVEL 2.  REMOVED AND REPLACED WITH SERVICEABLE UNIT V/S REPAIR FOR CUSTOMER CONVENIENCE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F      A16WE                        
20060530001182006053000118NM  2006       5          30         SROM200600014    120060524G575365522469        CARRIAGE                                BOEING737   737201      1384454NM                                                               WING            CORRODED        C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03245US     15552             22751                                   DURING HEAVY MAINTENANCE INSPECTION WHILE PERFORMING 10 YEAR CPCP INSPECTION REQUIREMENTS TO THE TRAILING EDGE FLAP CARRIAGES FOUND THE NR 5 CARRIAGE OTBD CARRIAGE HALF TO BE CORRODED.  LEVEL 2.  REPLACED WITH SERVICABLE UNIT V/S REPAIR FOR CUSTOMER CONVENIENCE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F      A16WE                        
20060530001222006053000122NM  2006       5          30         SROM200600015    120060524G575365522111        TORQUE TUBE                             BOEING737   737201      1384454NM                                                               ZONE 600        CORRODED        C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03245US     15552             22751                                   DURING HEAVY MAINTENANCE CHECK WHILE PERFORMING 10 YEAR CPCP REQUIREMENTS TO THE TRAILING EDGE FLAP CARRIAGES FOUND NR 5 FLAP CARRIAGE OUTER TORQUE TUBE TO BE CORRODED.  LEVEL 2.  REPLACED WITH SERVICABLE UNIT V/S REPAIR FOR CUSTOMER CONVENIENCE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F      A16WE                        
20060530001202006053000120NM  2006       5          30         SROM200600016    120060524G575365372061        TORQUE TUBE                             BOEING737   737201      1384454NM                                                               WING FLAP       CORRODED        C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03245US     15552             22751                                   DURING HEAVY MAINTENANCE CHECK WHILE PERFORMING 10 YEAR CPCP INSPECTION REQUIREMENTS TO THE TRAILING EDGE FLAP CARRIAGES FOUND THE NR 5 CARRIAGE INNER TORQUE TUBE TO BE CORRODED.  LEVEL 2.  REPLACED WITH SERVICEABLE UNIT V/S REPAIR FOR CUSTOMER CONVENIENCE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F      A16WE                        
20061115002462006111500246NM  2006       11         15         SROM200600017    120061109G32606552811109      ACCESSORY UNIT                          BOEING737   737205      1384456NM  PWA   JT8   JT8D17A     52049NE                              RT MLG          FAULTY          C  SROMA   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      AL03736BP                       23465                                   DURING DEPARTURE, UPON LANDING GEAR RETRACTION RT MLG INDICATION REMAINED RED.  MOVED LANDING GEAR HANDLE TO OFF AND THEN BACK TO UP, RED INDICATOR LIGHT REMAINED ON.  SELECTED GEAR DOWN AND GOT 3 GREEN AND NO RED.  RETURNED TO ANC WITH NORMAL LANDING.  WITH AIRCRAFT ON JACKS FOUND LANDING GEAR ACCESSORY UNIT TO BE FAULTY. REPLACED LANDING GEAR ACCESSORY UNIT AND ALL OPERATIONS CHECK NORMAL.  AIRCRAFT RELEASED WITH NORMAL OPERATIONS ON SUBSEQUENT FLIGHTS.                                                                                                                                                                                                                                                                     2L72 4F4  FRTA16WE   E2EA                 
20061213000052006121300005NM  2006       12         13         SROM200600018    120061130G5330                SKIN                                    BOEING737   737201      1384454NM                                                               FUSELAGE        MISREPAIRED     C  SROMK   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      AL03245US                       22751                                   DURING OWNER REQUEST FOR REPLACEMENT OF FUSELAGE SKIN BS 907 - 1016, STR 20L - 25L (P/N 65C80736-834) TO ELIMINATE PREVIOUS PERMANENT AND TEMPORARY SKIN REPAIRS, DISCOVERED NON-STANDARD REPAIR AT BS992.80, STR 20L IDENTIFIED AS A CUTOUT IN THE ADJACENT UPPER SKIN.  INSTALLED NEW REPAIR PER BOEING REPAIR INSTRUCTION 1-248459651-6, REFERENCE BOEING ISSUED FAA FORM 8100-9, DATED 30 NOV 2006.                                                                                                                                                                                                                                                                                                                                         2L72 4F      A16WE                        
20061213000402006121300040NM  2006       12         13         SROM200600019    120061203G5330                SKIN                                    BOEING737   737205      1384456NM                                                               BS 895          GOUGED          C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03733PA                       23466                                   ON POST FLIGHT INSPECTION FOUND THREE INCH SKIN GOUGE AT FUSELAGE BS 895 BETWEEN STRS 22R AND 23R.  REPAIRED WITH SKIN DOUBLER PER BOEING 737 SRM 53-30-3 AND 51-20-1.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA16WE                        
20061213000072006121300007NM  2006       12         13         SROM200600020    120061130G5521657378443       SPAR                                    BOEING737   737205      1384456NM                                                               ELEVATOR        CRACKED         C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03736BP     4604              23465                                   DURING INSPECTION FOUND LT ELEVATOR TAB OUTBOARD HINGE FITTING TO HAVE CONSIDERABLE FLEX.  UPON FURTHER EXAMINATION FOUND ELEVATOR REAR SPAR CRACKED IN THE AREA WHERE TAB HINGE FITTING ATTACHES.  AD 2006-14-07/SB 737-55A1078 HAD NOT BEEN ACCOMPLISHED PRIOR TO THIS FINDING.  REPLACED ELEVATOR AND TAB WITH NEW.                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA16WE                        
20070108001892007010800189NM  2007       1          8          SROM200600021    120061221G3220                LANDING GEAR                            BOEING737   737205      1384456NM  PWA   JT8   JT8D17A     52049NE                              NLG             CONTAMINATED    C  SROMA   UNSCHED LANDING                                                                                 J  WARNING INDICATION                                                            CLCLIMB          1                      AL03733PA                       23466                                   UPON DEPARTURE DURING HEAVY SNOW CONDITIONS WITH GRAVEL SKI EQUIPPED AIRCRAFT THE NOSE GEAR UNLOCK LIGHT REMAINED ON AFTER LANDING GEAR RETRACTION.  LANDING GEAR EXTENDED AND AIRCRAFT RETURNED TO DEPARTURE AIRPORT WITH NORMAL LANDING.  UPON INSPECTION FOUND GRAVEL DEFLECTOR TO BE CONTAMINATED WITH SNOW AND ICE.  REMOVED SNOW AND ICE, JACKED AIRCRAFT AND SWUNG GEAR WITH NO DEFECTS NOTED.  VERY HEAVY SNOW CONDITIONS ALLOWED FOR SNOW BUILD UP ON DEFLECTOR DURING TAXI OUT.  DEFLECTOR WAS DEICED PRIOR TO TAXI.                                                                                                                                                                                                                  2L72 4F4  FRTA16WE   E2EA                 
20070104000732007010400073NM  2007       1          4          SROM200600022    120061227G5753                CARRIAGE                                BOEING737   737201      1384454NM  PWA   JT8   JT8D15      52051NE                              SPINDLE         CRACKED         C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03245US     64                22751                                   DURING ROUTINE ACCOMPLISHMENT OF ULTRASOUND INSPECTION OF THE SPINDLES ON THE OB FLAPS IAW AD 2003-24-08 FOUND THE RT IB SPINDLE TO SHOW A CRACK INDICATION.  LAST ULTRASONIC INSPECTION PERFORMED 46 CYCLES AGO.  REPLACED SPINDLE AND CARRIAGE ASSEMBLY WITH NEW P/N 65C80736-712.                                                                                                                                                                                                                                                                                                                                                                                                                                                            2L72 4F4  F  A16WE   E2EA                 
20060530001522006053000152NM  2006       5          30         SRON200600007    120060516G5330                SKIN                                    BOEING737   737201      1384454NM                                                               FUSELAGE        MISDRILLED      C  SROMK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      AL03245US     1210              22751                                   DURING HEAVY MAINTENANCE INSPECTION FOUND SNOWMAN SHAPED HOLE WITH A SOLID AND CHERRY MAX IN IT AT STA 727A, STR 26L.  REPAIR PATCH AND DOUBLER INSTALLED PER BOEING ENGINEERING 1-185416133.  FAA FORM 8109-9.0                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                2L72 4F      A16WE                        
20060530001712006053000171EU  2006       5          30         THMN4113SQ116    120060508G5414MY2055270       COWLING                                 AMD   FALCONFALCON20    2730103EU                                                               ENGINE          CRACKED         B  T0DRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE03453SB                       308                                     RT INBOARD ENGINE COWL HAS SMALL CRACK IN SKIN AT TOP/FWD CORNER.  MADE AIRWORTHY REPAIR IAW DASSAULT FALCON 20 SRM 51-10-21.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   2L72 4F    RTA7EU                         
20060613003772006061300377EU  2006       6          13         THMN4113SQ118    120060508G5414MY20552302      COWLING                                 AMD   FALCONFALCON20    2730103EU                                                               RT ENGINE       CRACKED         B  T0DRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE03453SB                       308                                     RT UPPER ENGINE COWL SKIN CRACKED AT FWD SEAL BRACKET. MADE AIRWORTHY REPAIR IAW SRM 54-20-43.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  2L72 4F    RTA7EU                         
20060518002402006051800240EU  2006       5          18         THMN4113SQ120    120060508G5420MY20552302      COWLING                                 AMD   FALCONFALCON20    2730103EU                                                               ENGINE          CRACKED         B  T0DRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE03453SB                       308                                     RT UPPER ENGINE COWL AFT IB BRACKET CRACKED AT CORNER.   MADE AIRWORTHY REPAIR IAW SRM 54-20-43 AND SRM 51-10-22.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                               2L72 4F    RTA7EU                         
20060530001722006053000172EU  2006       5          30         THMN4113SQ121    120060508G5420MY20552302      COWLING                                 AMD   FALCONFALCON20    2730103EU                                                               ENGINE          CRACKED         B  T0DRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE03453SB                       308                                     R/H UPPER ENGINE COWL CRACKED IN BRACKET UNDER SEAL IN CENTER SECTION.  MADE AIRWORTHY REPAIR IAW FALCON 20 SRM 54-20-43.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F    RTA7EU                         
20060530001232006053000123CE  2006       5          30         THMN4129SQ111    120060522G5753                RIVET                                   CESSNA500   500CESSNA   2076602CE                                                               RT IB FLAP      LOOSE           B  T0DRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE0327SF                        64                                      RT INBOARD FLAP LOWER L/E HAS 7 LOOSE RIVETS.  REMOVED AND REPLACED RIVITS IAW SRM 51-30-1.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     1L72 4F      A22CE                        
20060530001572006053000157CE  2006       5          30         THMN4129SQ112    120060522G5730552280051       SKIN PANEL                              CESSNA500   500CESSNA   2076602CE                                                               LT WING         CRACKED         B  T0DRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE0327SF                        64                                      LT WING PANEL PN 5522800-51 CRACKED.  REPLACED PANEL IAW MM 57-30-00                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                            1L72 4F      A22CE                        
20060718001822006071800182SO  2006       7          18         THMN4165SQ117    120060630G5753                SKIN                                    PIPER PA30  PA39        7103902SO                                                               TE FLAP         CRACKED         B  T0DRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE03320GC                       3960                                    FLAP LT IB LWR SKIN CRACKED.  MADE AIRWORTHY REPAIR  IAW PA-39 SERVICE MANUAL, CHAPTER 4 PG 1F6 AND AC 43.13-1B SECTION 4 PARAGRAPH 4-57 FIGURE 4-6 AND SECTION 4 PARAGRAPH 4-58 FIGURE 4-16.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                   1L72 3O      A1EA                         
20060718001832006071800183SO  2006       7          18         THMN4165SQ118    120060630G5730                SKIN                                    PIPER PA30  PA39        7103902SO                                                               RT WING         CRACKED         B  T0DRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE03320GC                       3960                                    CRACK IN RT WING OB SKIN NEAR SPAR.  MADE AIRWORTHY REPAIR IAW PA-39 SERVICE MANUAL CHAPTER 4 PG 1F6 AND AC43.13-1B SECTION 4 PARAGRAPH 4-57 FIGURE 4-6 AND SECTION 4 PARAGRAPH 4-58 FIGURE 4-16                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                1L72 3O      A1EA                         
20060718001842006071800184SO  2006       7          18         THMN4165SQ123    120060630G5414                SKIN                                    PIPER PA30  PA39        7103902SO                                                               LT NACELLE      CRACKED         B  T0DRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE03320GC                       3960                                    LT ENGINE COWL CRACKED AT FWD FASTENER.  MADE AIRWORTHY REPAIR IAW PA-39 SRM CHAPTER 4 PG 1F6 AND AC43.13-1B SECTION 4 PARAGRAPH 4-57 FIGURE 4-6 AND SECTION 4 PARAGRAPH 4-58 FIGURE 4-16.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L72 3O      A1EA                         
20060815000072006081500007NM  2006       8          15         TL9R200600001    120060809G324626123111        WHEEL                                   BOEING737   737*               NM                                                               MLG             FRACTURED       B  TL9RO   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      NRNOT REPORTED   1                      GL13                                                                    OPERATOR STATES THAT SMOKE WAS REPORTED COMING FROM A WHEEL/BRAKE ASSEMBLY. TECHNICIANS DISCOVERED THAT THE HUB ON THE IB WHEEL HAD A COMPLETE CIRCUMFERENTIAL FRACTURE. THE COMPLETE WHEEL ASSEMBLY IS BEING SENT TO MFG FOR EVALUATION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       2L72 4F    RTA16WE                        
20060815000082006081500008NM  2006       8          15         TL9R200600002    120060809G324626123111        WHEEL                                   BOEING737   737*               NM                                                               ZONE 700        FRACTURED       B  TL9RO   OTHER                                                                                           B  SMOKE/FUMES/ODORS/SPARKS                                                      NRNOT REPORTED   1                      GL13                                                                    OPERATOR STATES THAT SMOKE WAS REPORTED COMING FROM A WHEEL/BRAKE ASSEMBLY. TECHNICIANS DISCOVERED THAT THE HUB ON THE IB WHEEL HAD A COMPLETE CRCUMFERENTIAL FRACTURE. THE COMPLETE WHEEL ASSEMBLY IS BEING SENT TO HONEYWELL IN SOUTH BEND, INDIANA FOR EVALUATION.                                                                                                                                                                                                                                                                                                                                                                                                                                                                           2L72 4F    RTA16WE                        
20061117001722006111700172EU  2006       11         17         TL9R200600003    120061116G3242C200601004      BRAKE                                   AIRBUS330   A300*              EU                                                               MLG             DEBONDED        B  TL9RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL13                                                                    OPERATOR/CUSTOMER REPORTED THIS BRAKE AS (BRAKE STUCK). SUBSEQUENT INSPECTION OF THE BRAKE AT THIS REPAIR STATION DOCUMENTED THAT THE TEMPERATURE SENSOR WAS BENT, AND PARTS OF THE HEAT STACK HAD DELINED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                     2L72 4F    RTA26NM                        
20060323001562006032300156CE  2006       3          23         UVVR200600001    120060221G5711NAS12913        NUT                                     RKWELLNA265 NA26560     7630106CE  PWA   JT12  JT12A8      52042NE                              WINGS           CRACKED         B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE0371CC                        30671                                   WHILE PERFORMING MAINTENANCE ON AIRCRAFT, IT WAS DISCOVERED THAT APPROXIMATELY 10 NUTS ON EACH WING THAT SECURES UPPER WING PLANK TO REAR SPAR UPPER FLANGE, FROM REAR SPAR STATION 161.1 TO 281.8 WERE CRACKED, WITH SOME MISSING PARTS OF THE NUT. AS A PRECAUTION, A TOTAL OF 96 SCREWS AND NUTS AT THESE LOCATIONS WERE REPLACED WITH NEW HARDWARE.                                                                                                                                                                                                                                                                                                                                                                                         2L72 4J4  JRTA2WE    1E9                  
20060323000562006032300056CE  2006       3          23         UVVR200600002    120060223G5744258WF71A        FITTING                                 RAYTHNDH125 HAWKER800XP 7150012CE                                                               LT WING         CORRODED        B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      CE03877DM3668                   258279                                  WHILE CHANGING A BONDING BRAID ON THE LT OB FLAP ATTACH FITTING, THE INNER SURFACE OF THE LOWER ATTACH POINT FLANGE WAS FOUND CORRODED.   APPROXIMATELY .050 INCH DEEP AROUND THE BOLT HOLE. THE PART WAS REPLACED WITH A NEW FITTING.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          2L72 4F    RTA3EU                         
20061018000452006101800045GL  2006       10         18         WI5R1005001      220061005G725073792           TURBINE BLADES                          CESSNA525   525         2076601CE  WILINTFJ44  FJ441A           GL                              ENGINE          FRACTURED       G  WI5RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      GL23103CS588  588               5250438     1903                        DURING A PRE-BUY A/C INSPECTION, ENGINE SN 1903 WAS FOUND TO EXHIBIT A FRACTURED TRAILING EDGE OF HP TURBINE BLADE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                             1L72 4F4  FRTA1WI    E3GL                 
20061031001682006103100168    2006       10         31         WL7R200600001    420061005G25641218FAUL03011   LIFE RAFT                                                                                                                                               UNSERVICEABLE   B  WL7RK   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      SO35                                                                    LIFE RAFT HAD A PARACHUTE CORD TIED AROUND THE INFLATABLE PORTION OF THE LIFE RAFT, WHICH WOULD HAVE CAUSED THE LIFE RAFT TO STRANGLE AND THE LIFE RAFT WOULD HAVE FAILED TO DEPLOY.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      
20061031001492006103100149    2006       10         31         WL7R200600002    420061005G25641218FAUL03011   LIFE RAFT                                                                                                                                               UNSERVICEABLE   B  WL7RK   NONE                                                                                            W  INADEQUATE Q C                                                                ININSP/MAINT     1                      SO35                                                                    LIFE RAFT HAD A PARACHUTE CORD TIED AROUND THE INFLATABLE PORTION OF THE LIFE RAFT, WHICH WOULD HAVE CAUSED THE LIFE RAFT TO STRANGLE AND THE LIFE RAFT WOULD HAVE FAILED TO DEPLOY.  PICTURE AVAILABLE.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                  
20061115002532006111500253WP  2006       11         15         WP07110306       220061103G72003103336         BEARING                                                                    GARRTTTPE331TPE3312U    01514WP                              ENGINE          FAILED          B  ZN3RE   ENGINE SHUTDOWN                                                                                 XJ ENGINE FLAMEOUT           WARNING INDICATION                                  CRCRUISE         1                      WP07     1566                               P70176C                     ENGINE WAS SENT TO MFG FOR A FLAME OUT INVESTIGATION. AT RECEIPT 2 KEY OBSERVATIONS WERE MADE. FIRST THE FILTER BYPASS INDICATOR WAS EXTENDED AND SECOND THE ROTATING GROUP WOULD NOT ROTATE. ONCE THE NOSE CONE AND DIAPHRAGM WERE REMOVED METAL WAS SEEN SHED THROUGHOUT GEARBOX. THE BINDING WAS FOUND TO BE DUE TO DAMAGE BETWEEN THE BULL GEAR AND HIGH SPEED PINION MATING TEETH. UPON FURTHER DISASSEMBLY, COMPRESSOR BEARING WAS DESTROYED. MFG BELIEVES THE COMPRESSOR BEARING AND NUT LOST THEIR FUNCTIONALITY, CAUSING THE ROTATING GROUP TO SHIFT FORWARD AND CAUSE RUBS. OVERALL THE SECONDARY DAMAGE DUE TO THIS EVENT WAS MINOR.                                                                                                        3  T          E3WE                 
20061020000422006102000042    2006       10         20         WSAOCT182006     420061018G3100704A46814049    LIGHT                                   SNIAS 350   AS350B3     8680954EU                                                               INSTRUMENT PANELCORRODED        B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW17578AE702                    3716                                    A TECHNICIAN REMOVED THE INSTRUMENT PANEL GRADUATOR, LIGHT (LIGHTING DIMMER) FOR ACCESS PURPOSES. IT WAS FOUND UPON REMOVAL THAT THE 24 PIN ELECTRICAL CONNECTOR ON THIS DIMMER HAD MODERATE CORROSION ON OVER HALF OF THE CONNECTOR PINS WITH SIGNS OF CORROSION ON THE PC BOARD. THE SOURCE OF THE CORROSION IS BELIEVED TO BE WATER INGRESS FROM THE FRESH AIR DUCT LOCATED ABOVE THIS PART.                                                                                                                                                                                                                                                                                                                                                 1G71 3U      H9EU                         
20060227001452006022700145CE  2006       2          27         WTXR10549        120060208G5340                ATTACH BRACKET                          LEAR  35    35A         5170602CE                                                               FUSELAGE        CRACKED         C  WTXRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW99                            113                                     FOUND CRACK AT LT AND RT FUSELAGE FRAME 20 AT THE WING ATTACH POINT.  LT CRACK IS APPROX 1.0 INCHES IN LENGTH, RT CRACK IS APPROX .75 INCHES IN LENGTH.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                         2L72 4F      A10CE                        
20060522002052006052200205SW  2006       5          22         YTRR109168       120060504G6520206033426001A   GEARBOX                                 BELL  206   206L4       1182110SW                                                               TAIL ROTOR      CRACKED         B  YTRRK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SW03410RL1387       52310       52310                                   DURING ROUTINE 100-HOUR AIRFRAME INSPECTION, FOUND TAIL ROTOR GEARBOX CASTING CRACKED.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                          1G71 3U    NCH2SW                         
20060330001002006033000100EA  2006       3          30         ZB0R200600001    220060309G8530                CYLINDER                                PIPER PA28  PA28R200    7102811SO  LYC   O360  O360C1C     41514EA                              ENGINE          SEPARATED       B  ZB0RE   ENGINE SHUTDOWN                                                                                 E  VIBRATION/BUFFET                                                              TXTAXI/GRND HDL  1                      SO0515143                       28R7335027  L958451A                    ON RUN-UP, PILOT AND INSTRUCTOR FELT ENGINE VIBRATION.  MAG DROPS WERE GOOD.  AIRPLANE WAS TAXIED TO MAINTENANCE.  MECHANIC FOUND NR 3 CYLINDER WITH 4 BROKEN MOUNT STUDS AND OIL COMING FROM EXHAUST.  CYLINDER REMOVED AND REPAIRED BY ENGINE SHOP.  ENGINE INSPECTION REVEALED NO FURTHER DAMAGE.  SUSPECT DETONATION AS CAUSE.                                                                                                                                                                                                                                                                                                                                                                                                              1L71 3O3  O  2A13    E286                 
20060807002412006080700241SO  2006       8          7          ZB0R20060001     120060725G324216402000        BRAKE DISC                              PIPER PA28  PA28236     7102815SO                                                               RT MLG          BROKEN          B  ZB0RO   OTHER                                                                                           O  OTHER                                                                         TXTAXI/GRND HDL  1                      SO05270SW     25                287911118                               ON LANDING ROLLOUT, PILOT LOST RIGHT BRAKING. MAINT DISCOVERED RIGHT BRAKE DISK BROKEN AT WELD COMPLETELY AROUND CIRCUMFERENCE. SUSPECT CORROSION ATTRIBUTED TO WELD FAILURE. PART REPLACED BY MAINT.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                           1L71 3O      2A13                         
20061020000962006102000096CE  2006       10         20         ZB0R20060002     120061016G32420500118127      LINE                                    CESSNA172   172S        2072439CE                                                               BRAKE SYSTEM    CORRODED        B  ZB0SO   OTHER                                                                                           S  AFFECT SYSTEMS                                                                NRNOT REPORTED   1                      SO053513K1147 15                172S8917                                DURING PREFLIGHT, PILOT NOTICED HYD FLUID COMING FROM RT BRAKE AREA. REPORTED TO MAINTENANCE. FOUND RT BRAKE LINE LEAKING. REMOVED LINE AND DISCOVERED PINHOLE CORROSION UNDER CHAFE PROTECTOR AT LOWER BEND OF LINE. SUSPECT WATER ENTERED CHAFE PROTECTOR AND CAUSED CORROSION. THE CHAFE PROTECTOR SHOULD BE SEALED AT EACH END TO PREVENT MOISTURE FROM ENTERING. REPLACED PART - OPS CK OK.                                                                                                                                                                                                                                                                                                                                                1H71 3O    NT3A12                         
20061204001092006120400109SO  2006       12         4          ZB0R20060003     120061120G272067174000        BAR                                     PIPER PA28  PA28R200    7102811SO                                                               RUDDER PEDALS   CRACKED         B  ZB0RK   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      SO05151434068 48                28R7335027                              DURING PROGRESSIVE INSPECTION, FOUND PILOT LT RUDDER BAR CROSS-OVER JOINT CRACKED AT WELD.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                      1L71 3O      2A13                         
20060203000822006020300082WP  2006       2          3          ZN3R556712       220060103G723030745557        STATOR                                  CESSNA650   650         2076802CE  GARRTTTPE731TFE7313C         WP                                              SEPARATED       B      K   NONE                                                                                            O  OTHER                                                                         ININSP/MAINT     1                      WP07650TA2556                   6500088     P87152C                     ENGINE 4TH LPC STATOR HAD INNER RING FRACTURE, LEADING TO A SINGLE VANE SEPARATING FROM THE STATOR ASSEMBLY.  THE VANE CAUSED DAMAGE TO THE HPC AREA OF THE ENGINE.  AIRCRAFT DID NOT EXPERIENCE ANY PROBLEMS WITH ENGINE DURING FLIGHT, AND PERFORMED SCHEDULED LANDING WITHOUT INCIDENT.                                                                                                                                                                                                                                                                                                                                                                                                                                                      2L72 4F4  F  A9NM    E6WE